Crossref Citations
This article has been cited by the following publications. This list is generated based on data provided by
Crossref.
CHENG, HSIEN K.
1963.
RECENT ADVANCES IN HYPERSONIC FLOW RESEARCH.
AIAA Journal,
Vol. 1,
Issue. 2,
p.
295.
Reshotko, Eli
1963.
Transition Reversal and Tollmien—Schlichting Instability.
The Physics of Fluids,
Vol. 6,
Issue. 3,
p.
335.
POTTER, J. LEITH
and
WHITFIELD, JACK D.
1964.
Comment on ''effects of controlled roughness on boundary-layer transition at a mach number of 6.0.'.
AIAA Journal,
Vol. 2,
Issue. 2,
p.
407.
Mabey, D. G.
1965.
Boundary Layer Transition Measurements Using a Surface Hot Film Downstream of Distributed Roughness at Mach Numbers from 1·3 to 4·0.
The Journal of the Royal Aeronautical Society,
Vol. 69,
Issue. 650,
p.
96.
NAGAMATSU, H. T.
and
SHEER, R. E.
1965.
Boundary-layer transition on a 10 deg cone in hypersonic flows..
AIAA Journal,
Vol. 3,
Issue. 11,
p.
2054.
RICHARDS, B. E.
and
STOLLERY, J. L.
1966.
Further experiments on transition reversal at hypersonic speeds..
AIAA Journal,
Vol. 4,
Issue. 12,
p.
2224.
Nagamatsu, H. T.
Graber, B. C.
and
Sheer, R. E.
1966.
Roughness, bluntness, and angle-of-attack effects on hypersonic boundary-layer transition.
Journal of Fluid Mechanics,
Vol. 24,
Issue. 1,
p.
1.
BACK, L. H.
MASSIER, P. F.
and
CUFFEL, R. F.
1966.
Some observations on reduction of turbulent boundary-layer heat transfer in nozzles..
AIAA Journal,
Vol. 4,
Issue. 12,
p.
2226.
RUSHTON, G.
1966.
Shock tunnel investigation of boundary-layer transition at M equals 5.5.
Hahn, Mansop
1966.
Pressure distribution and mass injection effects in the transitional separated flow over a spiked body at supersonic speed.
Journal of Fluid Mechanics,
Vol. 24,
Issue. 2,
p.
209.
McCAULEY, W. D.
SAYDAH, A. R.
and
BUECHE, J. F.
1966.
Effect of spherical roughness on hypersonic boundary-layer transition..
AIAA Journal,
Vol. 4,
Issue. 12,
p.
2142.
Richards, Bryan E.
1967.
Transitional and Turbulent Boundary Layers on a Cold Flat Plate in Hypersonic Flow.
Aeronautical Quarterly,
Vol. 18,
Issue. 3,
p.
237.
RUSHTON, GEORGE H.
and
STETSON, KENNETH F.
1967.
Shock tunnel investigation of boundary-layer transition at M equals 5.5..
AIAA Journal,
Vol. 5,
Issue. 5,
p.
899.
MASAKI, M.
and
YAKURA, J.
1968.
Transitional boundary layer considerations for the heating analyses of lifting reentry vehicles.
NAKAMURA, T.
1968.
Flight test measurements of boundary-layer transition on a nonablating 22 deg cone.
GRABER, B.
SOFTLEY, E.
and
ZEMPEL, R.
1968.
Experimental observation of transition of the hypersonic boundary layer.
MASAKI, M.
and
YAKURA, J. K.
1969.
Transitional boundary-layer considerations for the heating analyses of lifting re-entry vehicles..
Journal of Spacecraft and Rockets,
Vol. 6,
Issue. 9,
p.
1048.
SOFTLEY, E. J.
GRABER, B. C.
and
ZEMPEL, R. E.
1969.
Experimental observation of transition of the hypersonic boundary layer..
AIAA Journal,
Vol. 7,
Issue. 2,
p.
257.
HELLER, HANNO H.
1969.
Acoustic technique for detection of flow transition on hypersonic re-entry vehicles.
AIAA Journal,
Vol. 7,
Issue. 12,
p.
2227.
OWEN, F.
1969.
Transition experiments on a flat plate at subsonic and supersonic speeds.