Srinivas, K (1980) Computation of changes in the far flow field due to changes in the nose geometry of a typical fuselage. Technical Report. National Aerospace Laboratory, Bangalore, India.
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Abstract
Computations were carried out to determine the effect of changes in nose geometry of a typical fuselage on tho far flow field near the location of external stores where the flow is supersonic. The from stream Mach number was 1.5. r or the particular case considered it was found that the changes in geometry influence the flow field only in the vicinity of the shock and not far downstream where the stores are to be located.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Geometry;far flow foeld;aircraft models |
| Subjects: | AERONAUTICS > Aerodynamics |
| Division/Department: | Aerodynamics |
| Depositing User: | Deputy Head Poornima Narayana |
| Date Deposited: | 09 Aug 2006 |
| Last Modified: | 24 May 2010 09:48 |
| URI: | http://nal-ir.nal.res.in/id/eprint/2477 |
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