Inviscid Flow Field Computation of Hypervelocity Projectiles 881520
Inviscid flow fields have been computed for blunt axisymmetric shapes exposed to a hypersonic environment. A fully implicit scheme using a flux vector splitting technique was used to obtain a finite difference formulation. To increase computational efficiency, an approximate factorization scheme was used. Flow-field solutions were obtained for chemically reacting air using a decoupled approach. Flow fields were computed for blunted, flared shapes over a range of Mach numbers from 2 to 20.
Citation: Hoffmann, K., Bertin, J., and Chiang, T., "Inviscid Flow Field Computation of Hypervelocity Projectiles," SAE Technical Paper 881520, 1988, https://doi.org/10.4271/881520. Download Citation
Author(s):
Klaus A. Hoffmann, John J. Bertin, Ting-Lung Chiang
Affiliated:
The University of Texas at Austin
Pages: 10
Event:
Aerospace Technology Conference and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
Advanced Aerospace Aerodynamics-SP-0757, SAE Transactions Journal of Aerospace-V97-1
SAE MOBILUS
Subscribers can view annotate, and download all of SAE's content.
Learn More »
