Some Exploratory Pressure Measurements on a Blunt Plate with a Non-Equilibrium Flow Field,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1963
- Accession Number
- AD0715608
Entities
People
- R. E. Geiger
Organizations
- General Electric