Accession Number : AD0715608

Title :   Some Exploratory Pressure Measurements on a Blunt Plate with a Non-Equilibrium Flow Field,

Corporate Author : GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV

Personal Author(s) : Geiger,R. E.

Report Date : JAN 1963

Pagination or Media Count : 32

Abstract : A series of exploratory pressure measurements was made in the G. E. Space Sciences Laboratory's 30 inch shock tunnel on a cylindrically blunted flat plate at conditions where the expanding part of the model flow field is expected to be chemically frozen but where earlier nozzle static pressure data indicate the test section flow to be nearly in equilibrium. Analysis of the data and comparison with exact equilibrium flow field solution provided by Fitzgibbon and Edsall indicate that the expanding section of the model flow field is largely, perhaps completely, frozen. As a consequence, pressures behind the nose are significantly lower than for an equilibrium flow field resulting in a somewhat smaller loss of CL and L/D at low angles of attack. Flow separation renders impossible firm conclusions as to the non-equilibrium effects on the effectiveness of a windward deflected leading edge flap type control; however the data suggest reduced effectiveness at zero angle of attack for 10 degree and 20 degree deflections. (Author)

Descriptors :   (*FLAT PLATE MODELS, *FROZEN EQUILIBRIUM FLOW), SHOCK TUBES, FLOW FIELDS, SPECIFIC HEAT, ENTHALPY, STAGNATION POINT, EXPERIMENTAL DATA, PRESSURE, FLOW SEPARATION, ANGLE OF ATTACK, BLUNT BODIES

Subject Categories : Fluid Mechanics
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE