Design Analysis Summary Of Two Force-Balance Hypersonic Inlet Configurations

Item

Title
Design Analysis Summary Of Two Force-Balance Hypersonic Inlet Configurations
Date
1964
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
FDL TDR 64-19
Creator
Kutschenreuter, Paul H., Jr.
Balent, Richard L.
Richy, George K.
Corporate Author
Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio
Laboratory
Air Force Flight Dynamics Laboratory
Extent
48
Identifier
AD0437909
Access Rights
OTS
Distribution Classification
1
Contract
Laboratory Research - No Contract
DoD Project
1366
DoD Task
136605
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
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.
Report Availability
Full text available
Date Issued
1964-03
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource