Numerical Studies of the Ground Effect Vehicle Airfoil by the Mirroring Method

Aeronautical and Space-Rocket Engineering


Аuthors

Pavlenko O. V.1, 2*, Fevralskikh A. V.3**, Natur M. Z.4***

1. Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia
2. Moscow Institute of Physics and Technology (National Research University), 9, Institutskiy per., Dolgoprudny, Moscow region, 141701, Russia
3. Nizhny Novgorod State Technical University n.a. R.E. Alekseev, 24, Minin Street, Nizhny Novgorod, 603950, Russia
4. Moscow Institute of Physics and Technology (State University) (MIPT), 16, Gagarin St., Zhukovsky,140180, Russia

*e-mail: olga.v.pavlenko@yandex.ru
**e-mail: a.fevralskih@gmail.com
***e-mail: natourzaki@gmail.com

Abstract

The ground effect vehicle creation is an urgent task, since they are able to move both along the water and on various surfaces such as soil, snow or ice, as well as posess the ability of basing on these surfaces. Compared with water transport herewith, they possess a higher speed and a higher aerodynamic quality compared with airplanes. The problem of stability and controllability ensuring is being put forward as a rule as the main one while the ground effect vehicle designing.
A number of problems associated with correct description of the ground proximity effect impact with account for the moving screen arise while the ground effect vehicle studying in the wind tunnels. There are several techniques for the experimental study of the airfoil motion over the screen in the wind tunnels in this case. These are the screen modeling by the immovable wall, the mirror image method application or the movable wall method. Sucking-out of the boundary layer being formed with variable or constant consumption along the screen is possible as well.
One of the ways of the control system improving is mathematical modeling of the ground effect vehicle motion. As of today, the progress in software and numerical research methods applied at the preliminary design stage opens new possibilities in solving the problems on the ground effect vehicles creation and their updating.
The article presents the results of numerical study of the screen (ground) effect on the NASA 5312 wing airfoil flow-around by the mirror images method in comparison with the experimental results, as well computation of the Clark Y+ airfoil with both non-deflected (δflap = 0) and deflected twenty degrees deflected (δflap = 20°) flap.
The experiment, with which the numerical studies were compared, employed the mirror images method.
For this purpose, the two wing models were installed in the working part of the wind tunnel: the main (being studied) wing at the top and the auxiliary one at the bottom. The symmetry plane was employed in the numerical study of the NACA 5312 wing airfoil by the mirror images method. Experimental and computational dependencies of the lifting force on the height above the screen, expressed as a height above the ground to the chord of the airfoil (H/b) demonstrated a good fit.
The Clark Y+ airfoil with both non-deflected and deflected in the takeoff position flap was computed by the same technique and with the same initial conditions. Computational results revealed that the screen effect on the lifting force of the screen Clark Y+ airfoil with non-deflected flap was similar to the results obtained in the computation and experiment on the NACA 5312 airfoil.
Numerical studies of the ground proximity impact on the load-bearing properties of the NACA 5312 and Clark Y profiles revealed that the airfoil lifting force is affected simultaneously by such factors as the above ground level, the angle of attack and the flap deflection angle. Thus, while near screen movement at the distance of 0.1b the lifting force increases by 16% for the Clark Y+ airfoil with non-deflected flap (δflap = 0) within the range of angles of attack of 4° ≤ α ≤ 10°. While with the flap deflection of δflap = 20° near the screen the lifting force increase near 19% occurs within the angle of attack range of –2° ≤ α ≤ 6°.
Consequently, structural parts and screen parts interference should be considered in conjunction with the flight conditions, when the ground effect vehicle design to find the most optimal conditions of its motion.

Keywords:

Ground effect vehicle, aerodynamic characteristics, CFD-methods

References

  1. Ganin SM. Designing wing-in-ground effect aircraft from the 20th century to today. Transport Rossiiskoi Federatsii. Zhurnal o nauke, praktike, ekonomike. 2014(6):54-59. (In Russ.).
  2.  Pustoshnyi AV, Anosov VN, Ganin SM. et al. Prospects for the development of high-speed water transport in Russia. St. Petersburg: TsNII im. AN. Krylova; 2010. 124 p. (In Russ.).
  3.  Belavin NI. Ekranoplans. Leningrad: Sudostroenie; 1968. 176 p. (In Russ.).
  4.  Irodov RD. Criteria for longitudinal stability of an ekranoplane. Uchenye zapiski TsAGI. 1970;1(4):63-72. (In Russ.).
  5.  Belevin NI. Ekranoplans, according to the foreign press. 2nd ed. Leningrad: Sudostroenie; 1977. 230 p. (In Russ.).
  6.  Grumondz VT, Polishcuk MA, Chertorizhskaya SS. The choice of the pilotless plane vehicle dynamic image. Aerospace MAI Journal. 2024;19(4):5-12. (In Russ.).
  7.  Krivel' SM, Galushko EA. Influence of the layout parameters of the Tandem ekranoplane on its aerodynamic characteristics. Vestnik inzhenernoi shkoly DVFU. 2022(2):3–16. (In Russ.). DOI: 10.24866/2227-6858/2022-2/3-16
  8.  Sakornsin R, Popov SA. Optimization of the aerodynamics for the wing seaplane with floats on the end. Trudy MAI. 2012(57). (In Russ.). URL: https://trudymai.ru/eng/published.php?ID=31133
  9.  Qu Q, Wang W, Liu P, Agarwal RK. Airfoil aerodynamics in ground effect for wide range of angles of attack. AIAA Journal. 2015;53(4):1048–1061. DOI: 10.2514/1.J053366
  10.  Zhukov VI. Features of aerodynamics, stability and controllability of the ekranoplane. Moscow: Izdatel'skii otdel TsAGI; 1997. 30 p. (In Russ.).
  11.  Meshcheryakov IN. The design and operating conditions influence to stability of winged surface effect vehicle nearby supporting surface. Nauchnyi vestnik MGTU GA. 2010(151):175-180. (In Russ.).
  12.  Surzhik VV., Sankhorova AA. Self-stabilizing ekranoplanes of “DUCK” design with air cushion landing system. Vestnik IrGTU. 2014(6):74-78. (In Russ.).
  13.  Kudryashov AA. The study of the influence of adaptive wing panel on the longitudinal stability of ekranoplan. Aktual'nye problemy aviatsii i kosmonavtiki. 2017;2:470-473. (In Russ.).
  14.  Chirkov PR, Nikushkin NV. Adaptive wing systems in the appendix to security of aperiodic longitudinal ecranoplane stability a near to a reference surface. Sibirskii aerokosmicheskii zhurnal. 2007(3):82-84. (In Russ.).
  15.  Nazarov DV. Aerodynamics of an aircraft near the earth. Samara: Samarskii universitet; 2019. 120 p. (In Russ.).
  16.  Liverinova MA, Tryaskin NV. Numerical determination of aerodynamic characteristics of an airfoil in a ground effect. Morskie intellektual'nye tekhnologi. 2021;2(1-2):44-50. (In Russ.). DOI: 10.37220/MIT.2021.51.1.024
  17.  Bolotin AA. Mathematical modeling of WIG vehicle motion during its take-off run. Trudy NGTU im. RE. Alekseeva. 2013(5):283-286. (In Russ.).
  18.  Galushko EA, Krivel' SM. Evaluation of aerodynamic and flight performance characteristics of WIG with due consideration of the jet blowing from the propeller. Vestnik inzhenernoi shkoly DVFU. 2021;46(1):10-23. (In Russ.). DOI: 10.24866/2227-6858/2021-1-2
  19.   Luchkov АN. To the question of calculating the run distance of the lightweight WIG plan at the stage of preliminary design. IOP Conference Series: Materials Science and Engineering. Vol. 1027. Workshop on Materials and Engineering in Aeronautics (October 16-17, 2020; Moscow, Russia). DOI: 10.1088/1757-899X/1027/1/012016
  20.  Fevralskikh A, Makhnev M. Determination and analysis of roll and yaw rotary derivatives of WIG craft vehicle using numerical simulation. Aerospace Systems. 2023;6(3):151-156. DOI: 10.1007/s42401-022-00176-4
  21.   Qu Q, Lu Z, Liu P, Agarwal RK. Numerical Study of Aerodynamics of a Wing-in-Ground-Effect Craft. Journal of Aircraft. 2014;51(3):913-924. DOI: 10.2514/1.C032531
  22.  Mohid Z, Kamdani K, Ibrahim MR. et al. Aerodynamic Analysis of Wing-in-Ground (WIG) Effect Vehicle: Wing Profile and Orientation. Advances in Science and Technology. Vol. 136. 11th Asia Conference on Mechanical and Materials Engeneering (June 8-11, 2023; Sapporo, Japan). DOI: 10.4028/p-EtST7m
  23.  Hiemcke C. NACA 5312 in ground effect: wind tunnel and panel code studies. AIAA Journal. 1997. AIAA-97-2320, pp. 829-838.

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