Unified Computation Method of Unsteady Supersonic/Hypersonic Flow Past Two Dimensional Fiat Plate and Rectangular Wings 872447
Using perturbation method for the frequency to solve two dimensional unsteady Euler equations, we obtain the solutions of flat plate airfoil in pitching and plunging oscillations which are a set of power series including up to the sixth-order frequency term. The solutions are valid for low and higher frequency Cases (k∞ <1). With the aid of that solutions of airfoil and using supersonic linearized theory, the closed approximate expression of unsteady loading distribution is givers for rectangular wings in pitching and plunging oscillations. Thus, the computation method of this paper extends the application scope of Hui's(Refs.1,2) theory that hoMs for low frequency(k∞ ⪡1) pitching oscillation, Comparisons with supersonic linearized, Van Dyke and Lighthill theories are given.
Citation: Jing-song, C., Han-min, Y., and Cai-wen, Z., "Unified Computation Method of Unsteady Supersonic/Hypersonic Flow Past Two Dimensional Fiat Plate and Rectangular Wings," SAE Technical Paper 872447, 1987, https://doi.org/10.4271/872447. Download Citation
Chen Jing-song, Yang Han-min, Zhang Cai-wen
Dept. of Aerodynamics Nanjing Aeronautical Institute Nanjing, China
International Pacific Air and Space Technology Conference and Exposition
International Pacific Air and Space Technology Conference Proceedings-P-208