With the strong need of developing future aircrafts and other aerodynamics-related equipments, a general trend of developing new-generation airfoils is to achieve better multidisciplinary performance when flying at wider speed ranges, larger airspace and multi-physics enviroments or intelligent morphing, which presents great challenges for numerical simulations, design optimization, and experimental validations. The bionic concept of feather lift in birds under special flight conditions to control and reduce boundary layer separation is often applied to improve the performance of small aircraft or aircraft airfoils, 27 and this method is relatively seldom adopted in the research of flow separation control of wind turbine airfoil. Future challenges as well as research directions are presented as the outcome of this review. This article focuses on reviewing the recent progress on airfoil research after a brief review of over 100 years’ history of airfoil research and development. In the 21 st century, high-fidelity numerical simulations, multi-objective multi-constraint optimization, flow instability analysis theory and transition prediction methods, and experimental testing techniques have been advanced progressively, which places a sound base for the development of new-generation airfoils. A large number of airfoil families, such as RAE, DVL, NACA, and TsAGI, either for general purpose or for particular types of aircrafts flying at different speed regimes, as well as airfoil families dedicated to helicopter rotors, propeller blades, and wing-turbine blades have been developed. Since the invention of the first aircraft in the early 20th century, each breakthrough in airfoil research has dramatically promoted the upgrading of a better-performance aircraft. Canonsburg, Pennsylvania, USAĪnderson JD (1995) Computational fluid dynamics: the basics with applications.Airfoils, which are the cross-section profiles of aircraft wings and tails, missile fins, helicopter rotor blades, and wind turbine propellers, play a particularly important role in determining the aerodynamic and overall performance. Int J Eng Res Technol (IJERT) 7(3):366–373Īnsys Help Manual (2021) Ansys, Inc. Tharkude TS, Li DZ (2018) Simulation study of supersonic natural laminar flow on wing with biconvex airfoil. Manshadi MD, Aghajanian S (2018) Computational aerodynamic optimization of wing-design concept at supersonic conditions by means of the response surface method. Keith T, Cioc S, Jiang H (2019) Spreadsheet computations of a symmetric double wedge airfoil in supersonic flow. San Diego, USAĪskari S, Shojaeefard M, Goudarzi K (2011) Numerical and analytical solution of compressible flow over double wedge and biconvex airfoils. Hari N, Schetz JA, Kapania RK (2019) Numerical prediction of interference drag of a strut-surface intersection in supersonic flow. Hodson JD, Christopherson AP, Deaton JD, Pankoninen AM, Reich GW, Beran PS (2019) Aeroelastic topology optimization of a morphing airfoil in supersonic flow using evolutionary design methods. In: Proceedings of 9th international conference on computational fluid dynamics (ICCFD9), Istanbul, Turkey AIP Publishing, Turkey, pp 020002–1–020002–4Īkgun O, Golcuk AI, Kurtulus DF, Kaynak Ü (2016) Drag analysis of a supersonic fighter aircraf. In: AIP conference proceedings, vol 1935, no 1. Sogukpinar H (2018) Estimation of supersonic fighter jet airfoil data and low speed aerodynamic analysis of airfoil section at the Mach number 0.15. It is expected that wing changing geometry will be used not only for military but also for civil supersonic aircraft. ![]() Changing wing geometry could lead to less fuel consumption and less noise creation above urban places with airports inside the city area. This paper also promotes the wing morphing technologies due to increases in aerodynamical characteristics when the geometry changes. Also, for supersonic flight regime, the supersonic airfoil configuration provides over 10% higher value for C L/ C D ratio at 1° angle of attack based on the CFD results. ![]() It is shown how the maximum ratio of C L/ C D for subsonic configuration is 6.9, whereas for supersonic configuration under equal conditions, the max value for C L/ C D is 7.1, which is around 2.75% increase. The paper shows how a simple simulation-based analysis predicts better aerodynamical characteristics for a wing with changing geometry. The results are obtained with Reynolds averaged Navier–Stokes (RANS), and for resolving of the flow turbulence, the k- ω SST turbulence model was selected. The simulations were done using the Ansys Fluent 2021R Academic Version. Aerodynamic characteristics of the NACA 64A-204 airfoil are evaluated by numerical analysis of the turbulent flow at compressible and high Mach number using computational fluid dynamics (CFD).
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