SUPERSONIC AERODYNAMIC HEAT TRANSFER AND PRESSURE DISTRIBUTIONS ON A SPHERE-CONE MODEL AT HIGH ANGLES OF YAW
Abstract
Measurements of the static pressure and aerodynamic heat transfer on the surface of a spherecone model at Mach numbers of 3.23 and 4.83, and angles of yaw of 6 and 18 degrees were made. The results of several theoretical methods for calculating both the laminar and turbulent heat transfer to the body along the most windward and leeward streamlines are compared with the experimental measurements. The experimental laminar heat-transfer distributions are nearly alike for the two Mach numbers, when they are expressed in the form of the Nusselt number divided by the square root of the Reynolds number. The experimental heat-transfer data indicate that an increasing angle of yaw can induce transition from laminar to turbulent boundary layer.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1962
- Accession Number
- AD0284914
Entities
People
- Lionel Pasiuk
Organizations
- Naval Ordnance Laboratory