NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
On Reflection of Shock Waves from Boundary LayersMeasurements are presented at Mach numbers from about 1.3 to 1.5 of reflection characteristics and the relative upstream influence of shock waves impinging on a flat surface with both laminar and turbulent boundary layers. The difference between impulse and step waves is discussed and their interaction with the boundary layer is compared. General considerations on the experimental production of shock waves from wedges and cones and examples of reflection of shock waves from supersonic shear layers are also presented.
Document ID
19930090967
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Liepmann, H W
Roshko, A
Dhawan, S
Date Acquired
September 6, 2013
Publication Date
January 1, 1952
Report/Patent Number
NACA-TR-1100
Accession Number
93R20257
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available