Accession Number : AD0660574

Title :   A FACILITY FOR HYPERSONIC FLOW SIMULATION OVER BLUNT-NOSED BODIES.

Descriptive Note : Rept. for Jul-Dec 66

Corporate Author : NEW YORK UNIV N Y SCHOOL OF ENGINEERING AND SCIENCE

Personal Author(s) : Mak,Wing ; Zakkay,Victor

Report Date : JUL 1967

Pagination or Media Count : 73

Abstract : A facility for simulating re-entry flowfields over blunt-nosed bodies is presented. By using an H2O-O2 mixture it is shown that simulation of re-entry flowfields at the stagnation point may be achieved at lower stagnation temperatures. In this manner a large density ratio across the shock may be obtained without significantly altering the chemistry of the air. The criteria for simulation of supersonic flow over blunt-nosed bodies using any gaseous test medium were found to be the dynamic pressure and the density ratio across the normal shock. Combustion gases may be used as an aerodynamic test medium, provided that water vapor condensation is avoided and that equilibrium flow conditions are ensured. In the H2O-O2 mixture family, a mixture of equivalence ratio lambda = 0.2035 has been found to yield density ratios of the order of ten across a normal shock in equilibrium flow by suitably adjusting the pressure level. A buffered shock tunnel test facility is proposed to use the H2O-O2 mixture as the test medium. Flow Mach numbers of the order of ten can be attained at a static temperature of 300K. Operating conditions were determined for the heated air driver, the helium buffer and the H2O-O2 mixture, such that tailored condition of the reflected shock is achieved for maximum testing time. (Author)

Descriptors :   (*SHOCK TUBES, HYPERSONIC FLOW), (*HYPERSONIC FLOW, SIMULATION), (*ATMOSPHERE ENTRY, *FLOW FIELDS), GASES, MIXTURES, BLUNT BODIES, STEAM, OXYGEN, WATER VAPOR, CONDENSATION

Subject Categories : Aerodynamics
      Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE