Coandă effect

A spinning ping pong ball is held in a diagonal stream of air by the Coandă effect. The ball "sticks" to the lower side of the air stream, which stops the ball from falling down. The jet as a whole keeps the ball some distance from the jet exhaust, and gravity prevents it from being blown away.

The Coandă effect (/ˈkwɑːndə/ or /ˈkwæ-/) is the tendency of a fluid jet to stay attached to a convex surface.[1] A better definition has been provided by Henri Coandă in different patents and have been reported by Merriam Webster dictionary:[2] "the tendency of a jet of fluid emerging from an orifice to follow an adjacent flat or curved surface and to entrain fluid from the surroundings so that a region of lower pressure develops." The pressure effect, which is usually not indicated, is fundamental for the comprehension of the Coandă effect.

The principle was named after Romanian aerodynamics pioneer Henri Coandă, who was the first to recognize the practical application of the phenomenon in aircraft development.[3][4]

Discovery

An early description of this phenomenon was provided by Thomas Young in a lecture given to The Royal Society in 1800:

The lateral pressure which urges the flame of a candle towards the stream of air from a blowpipe is probably exactly similar to that pressure which eases the inflection of a current of air near an obstacle. Mark the dimple which a slender stream of air makes on the surface of water. Bring a convex body into contact with the side of the stream and the place of the dimple will immediately show the current is deflected towards the body; and if the body be at liberty to move in every direction it will be urged towards the current...[5]

A hundred years later, Henri Coandă identified an application of the effect during experiments with his Coandă-1910 aircraft, which mounted an unusual engine he designed. The motor-driven turbine pushed hot air rearward, and Coandă noticed that the airflow was attracted to nearby surfaces. In 1934 Coandă obtained a patent in France for a "method and apparatus for deviation of a fluid into another fluid." The effect was described as the "deviation of a plain jet of a fluid that penetrates another fluid in the vicinity of a convex wall." The first official documents that explicitly mention the Coandă effect were two 1936 patents by Henri Coandă.[6][7] This name was accepted by the leading aerodynamicist Theodore von Kármán, who had with Coanda a long scientific relationship on aerodynamics problems.[8]

The Coandă effect mechanism

The mechanism responsible for the Coandă effect
A diagram of a generic engine that harnesses the Coandă Effect to generate lift (or forward motion if tilted 90° on its side). The engine is approximately bullet or inverted bowl shaped, with fluid being expelled horizontally from a circular slit near the top of the bullet. A small step at the lower edge of the slit ensures that a low pressure vortex develops immediately below the point where the fluid exits the slit (see image 5 in the illustration on the left). From there on the Coandă effect causes the sheet of fluid to cling to the curved outer surface of the engine. The entrainment of the ambient fluid into the stream flowing over the bullet, causes a low pressure area above the bullet (see images 1-5 on the left) . This, together with the ambient ("high") pressure below the bullet causes lift, or, if mounted horizontally, forward motion in the direction of the apex of the bullet.[9]

A jet of air will entrain molecules of air from its immediate surroundings, causing a "tube," or "sleeve," of low pressure around the jet (see image 1 in the diagram on the left). Ambient air from around this tube of low pressure will exert a force on the jet, which, when seen in cross section, is equal in all directions. The jet will therefore not deviate from moving in a straight line. However, if a solid surface is placed close, and approximately parallel, to the jet (see image 2 in the diagram on the left), the entrainment (and therefore removal) of air from between the solid surface and the jet causes a reduction in air pressure on that side of the jet that cannot be neutralized as rapidly as the low pressure region on the "open" side of the jet. The pressure difference across the jet causes the jet to deviate towards the nearby surface, and then to adhere to it (image 3 on the left).[9][10] The jet will then adhere to the surface even if it is curved (image 4 on the left), because each (infinitesimally small) incremental change in direction of the surface will bring about the effects described for the initial bending of the jet towards the surface.[10][11] If the surface is not too sharply curved, the jet can, under the right circumstances, adhere to the surface even after flowing 180° round a cylindrically curved surface, and therefore be traveling in a direction opposite to its initial direction. The forces that cause these changes in the direction of flow of the jet cause an equal and opposite force on the surface along which the jet flows.[10] These Coandă effect induced forces can be harnessed to cause lift and other forms of motion, depending on the orientation of the jet and the surface to which the jet adheres.[9]

A small "lip" on the surface at the point where the jet starts to flow over that surface (see image 5 in the diagram on the left), enhances the initial deviation of the direction of flow of the jet, and its subsequent adherence to the surface. This results from the fact that a low pressure vortex forms behind the lip, promoting the dip of the jet towards the surface.[9]

The Coandă effect can be induced in any fluid, and is therefore equally effective in water as in air.[9]

Conditions of existence

Early sources provide information, both theoretical and experimental, needed to derive by comparison a detailed explanation of the Coandă effect and its limits. Coandă effect may occur along a curved wall either in a free jet or a wall jet.

On the left image of the preceding section: "The mechanism of Coanda effect", the effect as described, in the terms of T. Young as "the lateral pressure which eases the inflection of a current of air near an obstacle", represents a free jet emerging from an orifice and an obstacle in the surroundings. It includes the tendency of a free jet emerging from an orifice to entrain fluid from the surroundings confined with limited access, without developing any region of lower pressure when there is no obstacle in the surroundings, as is the case on the opposite side where turbulent mixing occurs at ambient pressure.

On the right image, the effect occurs along the curved wall as a wall jet. The image here on the right represents a two dimensional wall jet between two parallel plane walls, where the "obstacle" is a quarter cylindrical portion following the flat horizontal rectangular orifice, so that no fluid at all is entrained from the surroundings along the wall, but only on the opposite side in turbulent mixing with ambient air.

1. Wall jet. To compare experience with a theoretical model we first refer to a two-dimensional plane wall jet of width h along a circular wall of radius r. A wall jet follows a flat horizontal wall, say of infinite radius,or rather whose radius is the radius of the Earth without separation because the surface pressure as well as the external pressure in the mixing zone is everywhere equal to the atmospheric pressure and the boundary layer does not separate from the wall.

Measurements of surface pressure along a circularly curved wall of radius r = 12 cm, deflecting a turbulent jet of air (Reynolds number = 106) of width h. The pressure begins to fall before the origin of the jet, due to local effects at the point of exit of the air from the nozzle which creates the jet. If the h/r ratio (ratio of the width of the jet to the radius of curvature of the wall) is less than 0.5, a true Coandă effect is observed, with the wall pressures along the curved wall remaining at this low (sub-ambient pressure) level until the jet reaches the end of the wall (when the pressure rapidly returns to ambient pressure). If the h/r ratio is more than 0.5, only the local effects occur at the origin of the jet, after which the jet immediately separates from the wall, and there is no Coandă effect. Experiments by M. Kadosch and J. Liermann in M. Kadosch's laboratory, SNECMA.[12]

With a much smaller radius (12 centimeters in the image on the right) a transverse difference arises between external and wall surface pressures of the jet, creating a pressure gradient depending upon h/r, the relative curvature. This pressure gradient can appear in a zone before and after the origin of the jet where it gradually arises, and disappear at the point where the jet boundary layer separates from the wall, where the wall pressure reaches atmospheric pressure (and the transverse gradient becomes zero).

Experiments made in 1956 with turbulent air jets at a Reynolds number of 106 at various jet widths (h) show the pressures measured along a circularly curved wall (radius r) at a series of horizontal distance from the origin of the jet (see the diagram on the right).[12][13]

Above a critical h/r ratio of 0.5 only local effects at the origin of the jet are seen extending over a small angle of 18° along the curved wall. The jet then immediately separates from the curved wall. A Coandă effect is therefore not seen here but only a local attachment: a pressure smaller than atmospheric pressure appears on the wall along a distance corresponding to a small angle of 9°,followed by an equal angle of 9° where this pressure increases up to atmospheric pressure at the separation of the boundary layer, subject to this positive longitudinal gradient. However, if the h/r ratio is smaller than the critical value of 0.5, the lower than ambient pressure measured on the wall seen at the origin of the jet continues along the wall (till the wall comes to an end - see diagram on the right). This is a true Coandă effect as the jet clings to the wall at a nearly constant pressure "as in a conventional wall jet.

A calculation made by L. C. Woods in 1954[14] of an inviscid flow along a circular wall shows that an inviscid solution exists with any curvature h/r and any given deflection angle up to a separation point on the wall, where a singular point appears with an infinite slope of the surface pressure curve.

Pressure distribution along the circular wall of a wall jet

Introducing in the calculation the angle at separation found in the preceding experiments for each value of the relative curvature h/r, the image here was recently obtained,[15] and shows inertial effects represented by the inviscid solution: the calculated pressure field is similar to the experimental one described above, outside the nozzle. The flow curvature is caused exclusively by the transverse pressure gradient, as described by T. Young. Then, viscosity only produces a boundary layer along the wall and turbulent mixing with ambient air as in a conventional wall jet—except that this boundary layer separates under the action of the difference between the finally ambient pressure and a smaller surface pressure along the wall. According to Van Dyke,[16] quoted in Lift (force) Wikipedia article, §10.3, the derivation of his equation (4c) also shows that the contribution of viscous stress to flow turning is negligible.

An alternative way would be to calculate the deflection angle at which the boundary layer subjected to the inviscid pressure field separates. A rough calculation has been tried that gives the separation angle as a function of h/r and the Reynolds number:[13] The results are reported on the image, e.g., 54° calculated instead of 60° measured for h/r = 0.25. More experiments and a more accurate boundary layer calculation would be desirable.

Other experiments made in 2004 with a wall jet along a circular wall show that Coandă effect does not occur in a laminar flow, and the critical h/r ratios for small Reynolds numbers are much smaller than those for turbulent flow.[17] down to h/r=0.14 if Re=500 and h/r=0.05 if Re=100.

2. Free jet. L. C. Woods also made the calculation of the inviscid two-dimensional flow of a free jet of width h, deflected round a circularly cylindrical surface of radius r, between a first contact A and separation at B, including a deflection angle θ. Again a solution exists for any value of the relative curvature h/r and angle θ. Moreover in the case of a free jet the equation can be solved in closed form, giving the distribution of velocity along the circular wall. The surface pressure distribution is then calculated using Bernoulli equation. Let us note pa the pressure and va the velocity along the free streamline at the ambient pressure, and γ the angle along the wall which is zero in A and θ in B. Then the velocity v is found to be such that: v/va = exp[(2h/πr) tan−1[{sinh2 (πθr/4h) - cosh2(πθr/4h) tanh2(πγr/4h)}1/2]].

An image of the surface pressure distribution of the jet round the cylindrical surface using the same values of the relative curvature h/r, and the same angle θ as those found for the wall jet reported in the image on the right side here has been established: it may be found in reference (15) p. 104 and both images are quite similar : Coanda effect of a free jet is inertial, the same as Coanda effect of a wall jet. However, an experimental measurement of the corresponding surface pressure distribution is not known.

Experiences have been made in 1959 by C. Bourque and B. G. Newmann[18] concerning the reattachment of a two-dimensional turbulent jet to an offset parallel plate after enclosing a separation bubble where a low pressure vortex is confined, as in the image 5 in the preceding section ; and also for a two-dimensional jet followed by a single flat plate inclined at an angle instead of the circularly curved wall in the diagram on the right here describing the experience of a wall jet: the jet separates from the plate, then curves towards the plate when the surrounding fluid is entrained and pressure lowered, and eventually reattaches to it, enclosing a separation bubble. The jet remains free if the angle is greater than 62°.

In this last case which is the geometry proposed by Coanda, the claim of the inventor is that the quantity of fluid entrained by the jet from the surroundings is increased when the jet is deflected, a feature exploited to improve the scavenging of internal combustion engines, and to increase the maximum lift coefficient of a wing, as indicated in the applications below.

The surface pressure distribution as well as the reattachment distance have been duly measured in both cases, and two approximate theories have been developed for the mean pressure within the separation bubble, the position of reattachment and the increase in volume flow from the orifice: the agreement with experience was found fairly satisfactory.

Applications

The Coandă effect has important applications in various high-lift devices on aircraft, where air moving over the wing can be "bent down" towards the ground using flaps and a jet sheet blowing over the curved surface of the top of the wing. The bending of the flow results in aerodynamic lift.[19] The flow from a high speed jet engine mounted in a pod over the wing produces increased lift by dramatically increasing the velocity gradient in the shear flow in the boundary layer. In this velocity gradient, particles are blown away from the surface, thus lowering the pressure there. Closely following the work of Coandă on applications of his research, and in particular the work on his "Aerodina Lenticulară,"[20] John Frost of Avro Canada also spent considerable time researching the effect, leading to a series of "inside out" hovercraft-like aircraft from which the air exited in a ring around the outside of the aircraft and was directed by being "attached" to a flap-like ring.

The first Avrocar being readied at the Avro factory in 1958

This is as opposed to a traditional hovercraft design, in which the air is blown into a central area, the plenum, and directed down with the use of a fabric "skirt." Only one of Frost's designs was ever built, the Avrocar.

The VZ-9 AV Avrocar (often listed as VZ-9) was a Canadian vertical takeoff and landing (VTOL) aircraft developed by Avro Aircraft Ltd. as part of a secret United States military project carried out in the early years of the Cold War.[21] The Avrocar intended to exploit the Coandă effect to provide lift and thrust from a single "turborotor" blowing exhaust out the rim of the disk-shaped aircraft to provide anticipated VTOL-like performance. In the air, it would have resembled a flying saucer. Two prototypes were built as "proof-of-concept" test vehicles for a more advanced U.S. Air Force fighter and also for a U.S. Army tactical combat aircraft requirement.[22]

Avro's 1956 Project 1794 for the US military designed a larger-scale flying saucer based on the Coandă effect and intended to reach speeds between Mach 3 and Mach 4.[23] Project documents remained classified until 2012.

The effect was also implemented during the U.S. Air Force's AMST project. Several aircraft, notably the Boeing YC-14 (the first modern type to exploit the effect), NASA's Quiet Short-Haul Research Aircraft, and the National Aerospace Laboratory of Japan's Asuka research aircraft have been built to take advantage of this effect, by mounting turbofans on the top of the wings to provide high-speed air even at low flying speeds, but to date only one aircraft has gone into production using this system to a major degree, the Antonov An-72 "Coaler." The Shin Meiwa US-1A flying boat utilizes a similar system, only it directs the propwash from its four turboprop engines over the top of the wing to generate low-speed lift. More uniquely, it incorporates a fifth turboshaft engine inside of the wing center-section solely to provide air for powerful blown flaps. The addition of these two systems gives the aircraft an impressive STOL capability.

A Coandă engine (items 3,6-8) replaces the tail rotor in the NOTAR helicopter. 1 Air intake 2 Variable pitch fan 3 Tail boom with Coandă Slots 4 Vertical stabilizers 5 Direct jet thruster 6 Downwash 7 Circulation control tailboom cross-section 8 Anti-torque lift
A depiction of the Blackburn Buccaneer aircraft. The blowing slats visible on the leading edges and the wing and the trailing edge flaps are highlighted. These aerodynamic features contribute to the Coandă airflow over the wing
A diagram of the use of slats and flaps to increase the maximum lift coefficient of an airfloil. The extra lift coefficient is caused by the Coandă effect as the air is diverted through the openings in the wings caused by the extended slats and flaps. Extended slats and flaps are used on commercial aircraft on landing and taking off; but are also used to great effect on fighter aircraft to allow slow airspeeds when necessary. This is not an engineering drawing, but a somewhat exaggerated diagram to emphasize the major points.
The C-17 Globemaster III uses the Coandă effect in the same way as the Blackburn Buccaneer (depicted on the right), but with additional use of the exhaust from the engines over the upper surfaces of the wings to cause lift for a comfortable ride at low flying speeds

The McDonnell Douglas YC-15 and its successor, the Boeing C-17 Globemaster III, also employ the effect. The NOTAR helicopter replaces the conventional propeller tail rotor with a Coandă effect tail (diagram on the left).

A milestone in the direction of a better understanding of Coandă effect has been the large scientific literature produced by ACHEON EU FP7 project[24] This project about a particular symmetric nozzle has allowed an effective modeling of Coandă effect by Trancossi et al.[25][26] This model has been validated and relaborated by Das et al.,[27] Subhash[28] by assuming a more complex turbulence models and by Suñol et al.[29] This activity has led Trancossi to define precise design rules for the design of innovative STOL aircraft configurations,[30][31][32][33] and Das to a better and improved setup of the design of the novel UAS concept.[34] Work begun by Trancossi has been cited as a key reference in further research by Dragan in the turbomachinery sector, with the objective of better optimizing the shape of rotating blades by Rumanian Comoti Research Centre's work on turbomachinery.[35][36]

An important practical use of the Coandă effect is for inclined hydropower screens,[37] which separate debris, fish, etc., otherwise in the input flow to the turbines. Due to the slope, the debris falls from the screens without mechanical clearing, and due to the wires of the screen optimizing the Coandă effect, the water flows though the screen to the penstocks leading the water to the turbines.

The Coandă effect is used in dual-pattern fluid dispensers in automobile windshield washers.[38]

The operation principle of oscillatory flowmeters also relies on the Coandă phenomenon. The incoming liquid enters a chamber that contains two "islands." Due to the Coandă effect, the main stream splits up and goes under one of the islands. This flow then feeds itself back into the main stream making it split up again, but in the direction of the second isle. This process repeats itself as long as the liquid circulates the chamber, resulting in a self-induced oscillation that is directly proportional to the velocity of the liquid and consequently the volume of substance flowing through the meter. A sensor picks up the frequency of this oscillation and transforms it into an analog signal yielding volume passing through.[39]

In air conditioning, the Coandă effect is exploited to increase the throw of a ceiling mounted diffuser. Because the Coandă effect causes air discharged from the diffuser to "stick" to the ceiling, it travels farther before dropping for the same discharge velocity than it would if the diffuser was mounted in free air, without the neighbouring ceiling. Lower discharge velocity means lower noise levels and, in the case of variable air volume (VAV) air conditioning systems, permits greater turndown ratios. Linear diffusers and slot diffusers that present a greater length of contact with the ceiling exhibit a greater Coandă effect.

In cardiovascular medicine, the Coandă effect accounts for the separate streams of blood in the fetal right atrium.[40] It also explains why eccentric mitral regurgitation jets are attracted and dispersed along adjacent left atrial wall surfaces (so called "wall-hugging jets" as seen on echocardiographic color-doppler interrogation). This is clinically relevant because the visual area (and thus severity) of these eccentric wall-hugging jets is often underestimated compared to the more readily apparent central jets. In these cases, volumetric methods such as the proximal isovelocity surface area (PISA) method are preferred to quantify the severity of mitral regurgitation.

In medicine, the Coandă effect is used in ventilators.[41][42][43]

In meteorology, the Coandă effect theory has also been applied to some air streams flowing out of mountain ranges such as the Carpathian Mountains and Transylvanian Alps, where effects on agriculture and vegetation have been noted. It also appears to be an effect in the Rhone Valley in France and near Big Delta in Alaska.[44]

In Formula One automobile racing, the Coandă effect has been exploited by the McLaren, Sauber, Ferrari and Lotus teams, after the first introduction by Adrian Newey (Red Bull Team) in 2011, to help redirect exhaust gases to run through the rear diffuser with the intention of increasing downforce at the rear of the car.[45] Due to changes in regulations set in place by the FIA from the beginning of the 2014 Formula One season, the intention of redirecting exhaust gases to use the Coandă effect have been negated, due to the mandatory requirement that the car exhaust must not have bodywork directly behind the exit for use of aerodynamic effect.[46]

In fluidics the Coandă effect was used to build bistable multivibrators, where the working stream (compressed air) stuck to one curved wall or an other and control beams could switch the stream between the walls.

Demonstration

The Coandă effect can be demonstrated by directing a small jet of air upwards at an angle over a ping pong ball. The jet is drawn to and follows the upper surface of the ball curving around it, due to the (radial) acceleration (slowing and turning) of the air around the ball. With enough airflow, this change in momentum is balanced by the equal and opposite force on the ball supporting its weight. This demonstration can be performed using a vacuum cleaner if the outlet can be attached to the pipe and aimed upwards at an angle.

A common misconception is that Coandă effect is demonstrated when a stream of tap water flows over the back of a spoon held lightly in the stream and the spoon is pulled into the stream (for example, Massey in "Mechanics of Fluids"[47] uses the Coandă effect to explain the deflection of water around a cylinder). While the flow looks very similar to the air flow over the ping pong ball above (if one could see the air flow), the cause is not really the Coandă effect. Here, because it is a flow of water into air, there is little entrainment of the surrounding fluid (the air) into the jet (the stream of water). This particular demonstration is dominated by surface tension. (McLean in "Understanding Aerodynamics"[48] states that the water deflection "actually demonstrates molecular attraction and surface tension.")

An effective theoretical demonstration of the Coandă effect and of the possibility of modeling it is due to Trancossi who has defined a useful mathematical model that allow to produce a good prediction of different cases of Coanda adhesion of a fluid over a convex surface in the range 10–100 m/s.[25][49] With respect to other models, Trancossi has developed a complete analytical description of the phenomena, which is strictly based on a theoretical approach and has not considered the simplification of assuming an irrotational fluid model. The model considers a complete solution based on Bernoulli Law and clearly demonstrates analytically the existence of the adhesion phenomena in two cases a fluid stream exiting from a nozzle and a synthetic jet formed by two streams improving former theoretical demonstrations by Newman,[50][51] and Bradshaw.[52] This methods present a particular robustness by including the possibility of introducing different and more sophisticated turbulence models.

Another demonstration is to direct the air flow from, e.g., a vacuum cleaner operating in reverse, tangentially past a round cylinder. A waste basket works well. The air flow seems to "wrap around" the cylinder and can be detected at more than 180° from the incoming flow. Under the right conditions, flow rate, weight of the cylinder, smoothness of the surface it sits on, the cylinder actually moves. Note that the cylinder does not move directly into the flow as a misapplication of the Bernoulli effect would predict, but at a diagonal.

The effect can also be seen by placing a can in front of a lit candle. If one blows directly at the can, the air bends around it and extinguishes the candle.

Problems caused

The engineering use of Coandă effect has disadvantages as well as advantages.

In marine propulsion, the efficiency of a propeller or thruster can be severely curtailed by the Coandă effect. The force on the vessel generated by a propeller is a function of the speed, volume and direction of the water jet leaving the propeller. Under certain conditions (e.g., when a ship moves through water) the Coandă effect changes the direction of a propeller jet, causing it to follow the shape of the ship's hull. The side force from a tunnel thruster at the bow of a ship decreases rapidly with forward speed.[53] The side thrust may completely disappear at speeds above about 3 knots.[54] If the Coandă effect is applied to symmetrically shaped nozzles, it presents resonation problems. Those problems and how different spins couple has been analyzed in depth by Shyam, Pascoa et al.[34]

See also

References

  1. ↑ Tritton, D.J., Physical Fluid Dynamics, Van Nostrand Reinhold, 1977 (reprinted 1980), Section 22.7, The Coandă Effect.
  2. ↑ http://www.merriam-webster.com/dictionary/Coanda%20effect
  3. ↑ "The Coanda effect is a phenomenon that was first observed in 1910 by a mathematician and engineer named Henri Coandă. He discovered that when air was ejected from a rectangular nozzle, it would attach itself to an inclined flat plate connected to the nozzle exit. Emphasizing the need for a sharp angle between the nozzle and the flat plate, Coandă then applied the principle to a series of deflecting surfaces, each at a sharp angle to the previous one, and succeeded in turning flows through angles as large as 180. He stated that "when a jet of fluid is passed over a curved surface, it bends to follow the surface, entraining large amounts of air as it does so," and this phenomenon has become known as the Coandă Effect. On Some Recent Applications of the Coanda Effect Caroline Lubert International Journal of Acoustics and Vibration, Vol. 16, No. 3, 2011 http://www.iiav.org/ijav/content/volumes/16_2011_1739941303237209/vol_3/237_firstpage_856831320254369.pdf
  4. ↑ Coandă effect. (2013). Columbia Electronic Encyclopedia, 6th Edition. Digital version available here: http://www.answers.com/topic/coanda-effect archiveurl=https://web.archive.org/web/20120118131611/http://www.answers.com/topic/coanda-effect archivedate=2012-01-18
  5. ↑ The pressure of the air jet is actually supplementing the pressure of the atmosphere, aka The Atmospheric Press, which at 14.7psi at sea level makes water or other liquids lay smooth. Blow on a part of the water and the pressure is increased a slight amount which naturally makes the water move away. Direct a flame parallel over a liquid or submerge a candle almost to its wick and the liquid will be seen to rise slightly as the heat of the flame lessens the Atmospheric Press pressing on the water. The hotter the flame and the closer to the surface the greater the effect will be seen. Young, Thomas (1800), Outlines of experiments and inquiries respecting sound and light
  6. ↑ Coanda, H. "US Patent# 2,052,869." Device for Deflecting a Stream of Elastic Fluid Projected into an Elastic Fluid (1936).
  7. ↑ Coanda H. (1936a), US Patent n. 3,261,162, Lifting Device Coanda Effect, USA
  8. ↑ Eisner, Thomas (2005), For Love of Insects, Harvard University Press, p. 177, ISBN 0-674-01827-3
  9. 1 2 3 4 5 Reba, Imants (June 1966). "Applications of the Coanda effect". Scientific American. 214 (6): 84–921. doi:10.1038/scientificamerican0666-84.
  10. 1 2 3 Coanda Effect Retrieved 17 November 2017
  11. ↑ Jeff Raskin: Coanda Effect: Understanding how wings work. Retrieved 17 November 2017
  12. 1 2 Kadosch M., Déviation d’un jet par adhérence à une paroi convexe in Journal de Physique et le Radium, avril 1958, Paris, pp.1–12A
  13. 1 2 Kadosch M., "The curved wall effect" in 2nd Cranfield Fluidics Conference, Cambridge, 3 janvier 1967
  14. ↑ L. C. Woods, Compressible subsonic flow in two-dimensional channels with mixed boundary conditions, in Quart. Journ. Mech. And Applied Math., VII, 3, p. 263–282, 1954
  15. ↑ Kadosch M., Illusions créatrices, CreateSpace & Kindle,2015, Ch. 8, Coandă et le jet qui soulève les aeronefs, p. 91 to 112
  16. ↑ M. Van Dyke (1969), Higher-Order Boundary-Layer Theory, Annual Review of Fluid Mechanics
  17. ↑ T. Vit, F. Marsik, Experimental and Theoretical Study of Heated Coandă Jet, in XXI° International Congress of Theoretical and Applied Mechanics Warsaw, Poland, August 15–21, 2004
  18. ↑ Bourque, C. and Newmann, B. G.: Reattachment of a two-dimensional, incompressible jet to an adjacent flat Plate in: The Aeronautical Quarterly, vol XI, august 1960, pp.201 and seq.
  19. ↑ "Lift is a force generated by turning a moving fluid." Lift from Flow Turning NASA Glenn Research Center http://www.grc.nasa.gov/WWW/K-12/airplane/right2.html
  20. ↑ Fluid Dynamics by Mihaela-Maria Tanasescu, Texas Tech University
  21. ↑ Yenne 2003, pp. 281–283.
  22. ↑ Milberry 1979, p. 137.
  23. ↑ US Air Force's 1950s supersonic flying saucer declassified
  24. ↑ ACHEON-Aerial Coanda High Efficiency Orienting jet Nozzle, European Commission, Project reference: 309041, Funded under: FP7." TRANSPORT (2011).
  25. 1 2 Trancossi, M., Dumas, A., and Vucinic, D., "Mathematical Modeling of Coanda Effect," SAE Technical Paper 2013-01-2195, 2013, doi:10.4271/2013-01-2195
  26. ↑ Trancossi, Michele, et al. "Design methods of Coanda effect nozzle with two streams." INCAS Bulletin 6.1 (2014): 83. http://bulletin.incas.ro/files/trancossi__dumas__das__pascua__vol_6_iss_1.pdf
  27. ↑ Das, Shyam, et al. "Numerical modeling of Coanda effect in a novel propulsive system." The International Journal of Multiphysics 8.2 (2014): 181-202.
  28. ↑ Subhash, Maharshi, and Antonio Dumas. "Computational study of Coanda adhesion over curved surface." SAE International Journal of Aerospace 6.2013-01-2302 (2013): 260-272.
  29. ↑ Suñol, A., D. Vucinic, and S. Vanlanduit. "CFD Modelling of the Coanda Based Thrust Vectoring Nozzle." Engineering Applications of Computational Fluid Dynamics. Springer International Publishing, 2015. 73-84.
  30. ↑ Trancossi, Michele. Design of ACHEON thrust and vector propulsion system. No. 2015-01-2425. SAE Technical Paper, 2015.
  31. ↑ Trancossi, Michele, et al. "A new aircraft architecture based on the ACHEON Coanda effect nozzle: flight model and energy evaluation." European Transport Research Review 8.2 (2016): 1-21. https://link.springer.com/article/10.1007/s12544-016-0198-4
  32. ↑ Trancossi, Michele, et al. Preliminary implementation study of ACHEON thrust and vector electrical propulsion on a STOL light utility aircraft. No. 2015-01-2422. SAE Technical Paper, 2015.
  33. ↑ Trancossi, Michele, et al. Multifunctional unmanned reconnaissance aircraft for low-speed and STOL operations. No. 2015-01-2465. SAE Technical Paper, 2015.
  34. 1 2 Das, Shyam S., et al. "Computational Fluid Dynamic Study on a Novel Propulsive System: ACHEON and Its Integration with an Unmanned Aerial Vehicle (UAV)." Journal of Aerospace Engineering 29.1 (2015): 04015015.
  35. ↑ Dragan, V. (2014). Reynolds number calculation and applications for curved wall jets. INCAS Bull, 6(3), 35-41. http://bulletin.incas.ro/files/dragan__vol_6_issue_3.pdf
  36. ↑ Dragan, V. (2014). Notes regarding the definition and applicability of supercirculation. INCAS Bulletin, 6(2), 25. http://bulletin.incas.ro/files/dragan_v__vol_6__iss_2.pdf
  37. ↑ Hydropower in the U.S. Archived 2010-06-21 at the Wayback Machine., Coandă effect used in debris screen design.
  38. ↑ US 4210283 "Dual pattern windshield washer nozzle"
  39. ↑ Spitzer, David W. "Industrial Flow measurement." Instrument Society of America, 1990.
  40. ↑ Ashrafian H. The Coandă effect and preferential right atrial streaming. Chest. 2006 Jul;130(1):300.
  41. ↑ http://bja.oxfordjournals.org/content/100/6/859.full
  42. ↑ http://medical-dictionary.thefreedictionary.com/fluidic+ventilator
  43. ↑ http://www.japi.org/june_2009/16_MP_Anaestheisa_and_Critical_Care.pdf
  44. ↑ Giles, B.D. Fluidics, The Coandă Effect, and some orographic winds. Arch.Met.Geoph.Biokl. Ser.A. 25, 1977, 273–279
  45. ↑ Formula 1
  46. ↑ http://www.formula1.com/inside_f1/rules_and_regulations/sporting_regulations/12877/
  47. ↑ "Mechanics of Fluids, 4th edition 1979, Van Nostrand Reinhold Company, New York, ISBN 0-442-30245-2, Fig, 3.12
  48. ↑ "Understanding Aerodynamics Arguing from the Real Physics" Doug McLean, 2013, John Wiley & Sons Ltd. Chichester, ISBN 978-1-119-96751-4, Figure 7.3.6
  49. ↑ Trancossi M., Stewart J., Subash M., Angeli D., Mathematical model of a constructal Coanda effect nozzle, Journal of Applied Fluid Mechanics, 2016, Vol.9, No.8, pp 2813-2822. http://jafmonline.net/JournalArchive/download?file_ID=41384&issue_ID=237
  50. ↑ Newman, B. G., (1969) "The Prediction of Turbulent Jets and Wall Jets," Canadian Aeronautics and Space Journal, Vol. 15, pp. 287-305.
  51. ↑ Newman, B. G., (1961), "The Deflexion of Plane Jets by Adjacent Boundaries- Coanda Effect," Boundary Layer and Flow Control, edited by Lachmann, G. V., Vol. 1, Pergamon Press, Oxford, pp. 232–264.
  52. ↑ Bradshaw, P., (1973) "Effects of Streamline Curvature on Turbulent Flow," AGARDograph, AGARDograph AG-169.
  53. ↑ This problem can be solved by an accurate design of both the propeller and the hull that is specifically optimized on a fluiddynamic point of view. Lehn, E. (1992), Practical methods for estimation of thrust losses, Trondheim, Norway: Marintek (Norwegian Marine Technology Research Institute), report number 513003.00.06
  54. ↑ Clarke, I. C. (2005), Ship Dynamics for Mariners, London: The Nautical Institute
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