With the invention of the aircraft, it has become much faster and larger
than the original Wright Brothers aircraft. When the speed is high enough to
cross the speed of sound, air conditions will be different than that in low
speed due to the existence of shock wave. In this work, we introduce several
numerical ways to analyze the performance of the airfoil when the speed is
higher than the speed of sound. With these numerical methods, we analyzed the
performance of diamond-shaped airfoil under different angles of attack and
speed. With this data, engineers can choose a better airfoil to attain a lower
drag coefficient as well as lift coefficient when designing a high-speed
aircraft.
Henne, P.A. (Ed.) (1990) Applied Computational Aerodynamics. American Institute of Aeronautics and Astronautics.
[7]
Zheng, H.Y. (2012) Numerical Method.
[8]
Rao, V.M., Behal, A., Marzocca, P. and Rubillo, C.M. (2006) Adaptive Aeroelastic Vibration Suppression of a Supersonic Airfoil with Flap. Aerospace Science and Technology, 10, 309-315. https://doi.org/10.1016/j.ast.2006.03.006
[9]
Munk, M.M. (1950) The Reversal Theorem of Linearized Supersonic Airfoil Theory. Journal of Applied Physics, 21, 159-161. https://doi.org/10.1063/1.1699616
[10]
Puckett, A.E. (1946) Supersonic Wave Drag of Thin Airfoils. Journal of the Aeronautical Sciences, 13, 475-484. https://doi.org/10.2514/8.11425
[11]
Wakefield, G.H. (1970) U.S. Patent No. 3,497,163. U.S. Patent and Trademark Office, Washington, DC.
[12]
Gazley, C. (1956) Linearized Solution for Heat Addition at the Surface of a Supersonic Airfoil.
[13]
Wylly, A. (1952) A Second-Order Solution for an Oscillating Two-Dimensional Supersonic Airfoil. Journal of the Aeronautical Sciences, 19, 685-696.
https://doi.org/10.2514/8.2430
[14]
Wakefield, G.H. (1971) U.S. Patent No. 3,596,852. U.S. Patent and Trademark Office, Washington, DC.
