Accession Number : AD0634600

Title :   SHOCK-SHOCK INTERACTION THEORY INCLUDING REAL GAS AND THREE DIMENSIONAL EFFECTS.

Descriptive Note : Final rept.,

Corporate Author : AERONUTRONIC DIV PHILCO CORP NEWPORT BEACH CALIF

Personal Author(s) : Taylor, Thomas D.

Report Date : APR 1966

Pagination or Media Count : 75

Abstract : The report presents a numerical technique which can be employed to study the interaction of two nearly planar shock waves. The technique is applied to the head-on interaction of a blast wave and a bow shock of a re-entry vehicle. The application is limited to the axis of symmetry of the flow field. Real gas effects are included by allowing gamma (the adiabatic gas constant) to vary across flow discontinuities. The values of gamma are determined from curve fits to Gilmore's Tables. Three dimensional effects are incorporated in the study by using re-entry flow field calculations to obtain velocity gradients and flow conditions behind the re-entry bow shock. A computer program for the IBM 7090-94 which was developed to perform the shock-shock interaction study is given. (Author)

Descriptors :   (*SHOCK WAVES, BLAST), (*ATMOSPHERE ENTRY, SHOCK WAVES), (*REENTRY VEHICLES, ATMOSPHERE ENTRY), NUMERICAL ANALYSIS, COMPUTER PROGRAMMING

Subject Categories : Fluid Mechanics
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE