Supersonic flow past an axisymmetric body with combustion in separation zones at the body nose and base
A.I. Zubkov1, A.F. Garanin2, V.F. Safronov3, L.D. Sukhanovskaya1, and P.K. Tretyakov2
1Institute of Mechanics, Lomonosov Moscow State University, Moscow, Russia
2Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
3State Unitary Enterprise FNPC "Pribor", Moscow, Russia
Pages: 1-12
Abstract
The paper presents results of experimental study of aerodynamic characteristics of axisymmetric bodies with external mass injection and combustion. The flow structure was studied for bodies with separation zones on the nose and base parts of the body with different shapes. The influence of several parameters on supersonic flow was considered: freestream parameters, supply of inert or chemically reactive mass, physical and chemical parameters of fuel. The generalized relationships were developed for calculation of the nose and base drag that take into account the mass injection and combustion in supersonic flow.
|
