An overview of some investigations of pressure and thermal distributions induced by trailing edge controls on hypersonic aircraftDetailed surface heat transfer and pressure distributions have been obtained in three-dimensional shock-wave boundary-layer interactions flow regions. The data described were obtained on fundamental shapes: planar wings with trailing edge flaps or spoilers and planar or cylindrical center bodies, representative of the aft portion of hypersonic aircraft. An overview of the work is presented; details of the projects are available in many reports in the open literature. Analytic, empiric methods are advanced for predicting the extent of separation and the increased heat transfer and pressure loads in three-dimensional separated flow regions.
Document ID
19880063952
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Kaufman, Louis G., II (Grumman Corp. Bethpage, NY, United States)
Johnson, Charles B. (NASA Langley Research Center Hampton, VA, United States)