Design Analysis Summary Of Two Force-Balance Hypersonic Inlet Configurations
Report Number: FDL TDR 64-19
Author(s): Kutschenreuter, Paul H., Jr., Balent, Richard L., Richy, George K.
Corporate Author(s): Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 48
Contract: Laboratory Research - No Contract
DoD Project: 1366
DoD Task: 136605
Identifier: AD0437909
Abstract:
Two hypersonic inlet models were designed for force balance testing in the Cornell Aeronautical Laboratory 48-inch shock tunnel over a Mach Number range of 8 to 16. The performance of these models is to be established experimentally on the basis of their measured internal drag. Reasons for considering this method of establishing hypersonic inlet performance and use of the associated drag equivalent pressure recovery are discussed. The design of these models, the resulting inlet geometry, and the related performance caluclations are described.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Kutschenreuter, Paul H., Jr., Balent, Richard L., Richy, George K.
Corporate Author(s): Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 48
Contract: Laboratory Research - No Contract
DoD Project: 1366
DoD Task: 136605
Identifier: AD0437909
Abstract:
Two hypersonic inlet models were designed for force balance testing in the Cornell Aeronautical Laboratory 48-inch shock tunnel over a Mach Number range of 8 to 16. The performance of these models is to be established experimentally on the basis of their measured internal drag. Reasons for considering this method of establishing hypersonic inlet performance and use of the associated drag equivalent pressure recovery are discussed. The design of these models, the resulting inlet geometry, and the related performance caluclations are described.
Provenance: Lockheed Martin Missiles & Fire Control