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boundary-layer transition on a group of blunt nose shapes at a mach number of 2.20An investigation has been made to study boundary-layer transition on six axisymmetrical blunt bodies of revolution. Model shapes were selected with respect to the degree of favorable pressure gradient over the model surface. Tests were conducted at a Mach number of 2.20 and over a range of free-stream Reynolds number per foot of about 1.4 x 10(exp 6) to 6.5 x 10(exp 6). The tests were made at an angle of attack of 0 deg. with zero heat transfer. For the hemisphere, the flow remained essentially laminar over the model surface length for the entire pressure range of the tests. For a strong favorable pressure gradient followed by any weak favorable, neutral, or adverse gradient, the tendency was for transition to occur at or immediately behind the shoulder. A single strip of three-dimensional roughness in the region of strong favorable pressure gradient did not fix transition on the models at the roughness location except at the maximum test pressures, whereas a second roughness strip added in a region of neutral or adverse pressure gradient did fix transition. Experimental pressure coefficients agreed closely with modified Newtonian theory except in the shoulder region.
Document ID
19980227788
Document Type
Other - NASA Technical Note (TN)
Authors
Jackson, Mary W.
(NASA Langley Research Center Hampton, VA United States)
Czarnecki, K. R.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1961
Subject Category
Fluid Mechanics and Heat Transfer
Report/Patent Number
L-1383
NASA-TN-D-932
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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