![]() An essential ingredient of the understanding of supersonic flow is the calculation of the shape and strength of shock waves, such as those illustrated in Fig. 8 that as the freestream Mach number increases, the shock wave moves closer to the body and the sonic line moves down closer to the centerline of the flow. ![]() 8 divide the subsonic and supersonic regions behind the shock and are called the sonic lines, since the local Mach number M = 1 along these lines. The lower part of the flow field behind the shock wave is locally subsonic, and the upper part, after sufficient expansion around the body, is locally supersonic, albeit at a Mach number lower than M ∞. Two such shocks are shown to the left of the body the leftmost shock illustrates the case for M ∞ = 4, and the rightmost shock pertains to the case for M ∞ = 8. Flow is moving from left to right.If the upstream flow is supersonic ( M ∞ > 1), then a curved shock wave will exist slightly upstream of the blunt nose. ![]() For example, consider the blunt-nosed, parabolically shaped body shown at the right in Fig. ![]() In any steady flow where M > 1, shock waves can occur.
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |