National Advisory Committee for Aeronautics (NACA) - 1 Matching Results
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- Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model
- From Introduction: "The heat-transfer data calculated from measured temperatures are compared with values calculated by the theory of Van Driest for a flat plate with laminar and turbulent boundary layers. In addition, the heat-transfer data from the flight tests are compared with data obtained from the Langley Structures Research Division of ground tests of an identical wing at a Mach number approximately equal to 1.99 in the pre-flight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The stream static pressure is maintained at about 1 atmosphere, the free-stream temperature at about 75^o F, and the stagnation temperature at approximately 500 ^o F (ref.1)."