Stagnation Point Heat Transfer in High Enthalpy Gas Flows, Part I: Convective Heat Transfer in Partially Ionized Air
Report Number: FDL TDR 64-41 Part 1
Author(s): Nerem, Robert M., Stickford, George H.
Corporate Author(s): Ohio State University
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 48
Contract: AF 33(657)-10110
DoD Project: 1366
DoD Task: 136615
Identifier: AD0601370
Abstract:
Using an arc driven shock tube facility, measurements of convective heat transfer at the stagnation point of a blunt body were carried out at simulated flight velocities ranging from 20,000 to 40,000 feet per second. These measurements were performed using standard calorimeter techniques with air as the test media. The results indicate no significant ionization effects on aerodynamic heating and indicate that the Lee's approximate equation for stagnation point heat transfer can be used for engineering calculations at flight velocities up to 40,000 feet per second.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Nerem, Robert M., Stickford, George H.
Corporate Author(s): Ohio State University
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 48
Contract: AF 33(657)-10110
DoD Project: 1366
DoD Task: 136615
Identifier: AD0601370
Abstract:
Using an arc driven shock tube facility, measurements of convective heat transfer at the stagnation point of a blunt body were carried out at simulated flight velocities ranging from 20,000 to 40,000 feet per second. These measurements were performed using standard calorimeter techniques with air as the test media. The results indicate no significant ionization effects on aerodynamic heating and indicate that the Lee's approximate equation for stagnation point heat transfer can be used for engineering calculations at flight velocities up to 40,000 feet per second.
Provenance: Lockheed Martin Missiles & Fire Control