Numerical Computation of Base Flow for a Projectile at Transonic Speeds
- 1 June 1983
- report
- Published by Defense Technical Information Center (DTIC)
Abstract
The generalized-Axisymmetric Thin-Layer Navier-Stokes computational technique has been modified for projectile base flow analysis. The resulting new numerical capability is used to compute the entire projectile flow field including the recirculatory base flow. Computed results show the qualitative and quantitative details of the overall base flow structure. Base drag is computed for a secant-ogive-cylinder projectile at an angle of attack of zero and compared with available experimental data and a semi-empirical analysis. Results are also presented which show pressure drag, skin friction drag and total aerodynamic drag for Mach No. .9 M 1.2.Keywords
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