TWO-SHOCK INTERACTION IN A REGION OF NONUNIFORM FLOW.
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB
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The interaction of a plane blast wave with the nonuniform shock layer of a hypersonic blunted wedge is calculated using the method of characteristics, and the properties behind the reflection of the refracted blast wave from the wedge surface are found. The calculations are carried out for both a perfect gas and for air in thermodynamic equilibrium, including the effects of dissociation and ionization, and for uniform and nonuniform shock layers. A description is given of the FORTRAN computer program which was developed to perform the numerical calculations. A study is made of the influence of the nonuniform shock layer on the surface pressure at the blast wave reflection point it is found that a substantial change in surface pressure results from the nonuniformity of the shock layer under certain flight conditions which are characteristic of a re-entry vehicle. Author
- Fluid Mechanics
- Spacecraft Trajectories and Reentry