A Comparative Study of Numerical Versus Analytical Waverider Solutions
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The WLFIMM explicit, Roe flux-splitting Euler algorithm is applied to the inviscid hypersonic flow over a parabolic-top waverider configuration optimized for Mach 10 at zero degrees angle of attack. An on-design grid refinement study is conducted to determine the asymptotic nature of the optimized flight parameter LD. A parametric study of off-design conditions is conducted to determine flow perturbation effects on HSDT waverider theory. A validation of the Euler code is conducted through a comparison of the numerical data to analytical results derived by Rasmussen. The grid refinement study shows little effect on the inviscid calculation of the optimized parameter LD. Good agreement with HSDT waverider theory was attained for the on and off-design evaluations. Approximations involved in the numerical modeling of the waverider design produce large losses of lift as compared to the analytical results. Matching of the analytical results was possible only through a theoretical modeling process.
- Research and Experimental Aircraft
- Fluid Mechanics