Newtonian flow over delta wings with attached shock waves. (English) Zbl 0633.76059
A. F. Messiter’s thin shock layer theory for supersonic flow over delta wings [AIAA J. 1, 794-801 (1963; Zbl 0115.207)] is extended to the case of a shock wave attached along the leading edges. The explicit solution for the problem with a complex flow field is obtained and transformed to applicable expressions. Examples of calculations and a brief summary of the original theory are given.
Reviewer: E.F.Zhigalko
MSC:
76K05 | Hypersonic flows |
76L05 | Shock waves and blast waves in fluid mechanics |
76J20 | Supersonic flows |
35L40 | First-order hyperbolic systems |
35L45 | Initial value problems for first-order hyperbolic systems |
35L67 | Shocks and singularities for hyperbolic equations |