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Compressible Boundary Layer Equations And Stagnation Point Solution With Differences In Thermal And Dynamic Boundary Layer Thicknesses Being Considered

Report Number: ASD TR 61-107
Author: Buck, Melving L.
Corporate Author: Aeronautical Systems Div Wright-Patterson AFB Ohio Flight Control Lab
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1961-08
Pages: 45
Contract: Laboratory Research - No Contract
Project: 1366
Task: 14017
AD Number: AD0268584

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Lockheed Martin Missiles & Fire Control
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