TURBULENT REFERENCE, ROUGHNESS, LEAKAGE AND DEFLECTED-SURFACE HEAT TRANSFER AND PRESSURE TESTS FOR TBC
Abstract
Hypersonic tests of three basic models were conducted in the CAL 48-inch Hypersonic Shock Tunnel. The tests were run in the 23-inch and 46-inch exit-diameter contoured nozzles of the CAL Tunnel. The three models were: a blunt leading-edge model with sweep angles of 55, 60 and 65 degrees; a hemisphere-cylinder model; and a sharp flat plate with deflectable rear flap and span extensions. The objectives of the tests were as follows: (1) to obtain fully turbulent heat transfer rate and pressure data for leading edge, nose and flat surfaces with stream-to-wall property ratios characteristic of Dyna Soar flight conditions; (2) to establish the effect of transverse pressure gradient on roughness and leakage effects with laminar and turbulent boundary layer flow; (3) to defire heat transfer, pressure distribution and region of separation for aerodynamic control surfaces; and (4) to determine the variation in pressure and heat transfer rate distributions with model attitudes.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 27, 1963
- Accession Number
- AD0406248
Entities
People
- R. K. Ellison
Organizations
- Boeing