Three Dimensional Solution of Pneumatic Active Control of Forebody Vortex Asymmetry
- Author
- Kandil, Osama A.
- Published
- 1995.
- Physical Description
- 1 electronic document
- Additional Creators
- Liu, C. H. and SharafEl-Din, Hazem H.
Online Version
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- Restrictions on Access
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary
- Pneumatic active control of asymmetric vortical flows around a slender pointed forebody is investigated using the three dimensional solution for the compressible thin-layer Navier-Stokes equation. The computational applications cover the normal and tangential injection control of asymmetric flows around a 5 degree semi-apex angle cone at a 40 degree angle of attack, 1.4 freestream Mach number and 6 x 10(exp 6) freestream Reynolds number (based on the cone length). The effective tangential angle range of 67.5 approaches minus 67.5 degrees is used for both normal and tangential ports of injection. The effective axial length of injection is varied from 0.03 to 0.05. The computational solver uses the implicit, upwind, flux difference splitting finite volume scheme, and the grid consists of 161 x 55 x 65 points in the wrap around, normal and axial directions, respectively. The results show that tangential injection is more effective than normal injection.
- Other Subject(s)
- Collection
- NASA Technical Reports Server (NTRS) Collection.
- Note
- Document ID: 19970005048.
Accession ID: 97N13034.
NASA-CR-203089.
NAS 1.26:203089.
AIAA Paper 95-0101.
Aerospace Sciences; 9-12 Jan. 1995; Reno, NV; United States. - Terms of Use and Reproduction
- Copyright, Distribution as joint owner in the copyright.
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