MEASUREMENTS OF AERODYNAMIC HEAT TRANSFER AND BOUNDARY-LAYER TRANSITION ON A 10 DEGREE CONE IN FREE FLIGHT AT SUPERSONIC MACH NUMBERS UP TO 5.9
Abstract
The range of local Reynolds number was from 6.6 x 10 to the 6th power to 55.2 x 10 to the 6th power. In general, measurements were in good agreement with theory for cones. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 10 to the 6th power to 19.4 x 10 to the 6th power as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperature. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1961
- Accession Number
- AD0255850
Entities
People
- Charles B. Rumsey
- Dorothy B. Lee
Organizations
- National Aeronautics and Space Administration