Preliminary investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61
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Czarnecki, K R↗
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An Extension of the Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61
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Czarnecki, K R↗
Experimental Determination of Boundary-layer Transition on a Body of Revolution at M = 3.5
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Jedlicka, James R↗
Subsonic investigation of effects of body indentation on zero-lift drag characteristics of a 45 degree sweptback wing-body combination with natural and fixed boundary-layer transition through a range of Reynolds number from 1 x 10(exp 6) to 8 x 10(ex
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Braslow, Albert L↗
A Review of Recent Information on Boundary-layer Transition at Supersonic Speeds
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Seiff, Alvin↗
Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers up to 5.9
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Rumsey, Charles B↗
Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers up to 5.2
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Rumsey, Charles B↗
Experimental Investigation of the Effect of Boundary-layer Transition on the Average Heat Transfer to a Yawed Cylinder in Supersonic Flow
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Beckwith, Ivan E↗
Effect of Mach Number on Boundary-layer Transition in the Presence of Pressure Rise and Surface Roughness on an Ogive-cylinder Body with Cold Wall Conditions
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Carros, Robert J↗
Measurements of Boundary-layer Transition at Low Speed on Two Bodies of Revolution in a Low-turbulence Wind Tunnel
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Boltz, Frederick W↗
Investigation of Boundary-layer Transition on Flat-faced Bodies of Revolution at High Supersonic Speeds
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Canning, Thomas N↗
Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers up to 3.14 and Reynolds Numbers up to 24 x 10(exp 6)
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Buglia, James J↗
Aerodynamic Heating and Boundary-Layer Transition on a 1/10-Power Nose Shape in Free Flight at Mach Numbers up to 6.7 and Free-Stream Reynolds Numbers up to 16 x 10(exp 6)
A modified 1/10-power nose shape has been tested in free flight at Mach numbers up to 6.7 and free - stream Reynolds numbers based on diameter up to 16 X 10(exp 6). Measured heating rates were presented and compared with calculated values. Agreement ranges from poor on the forward portion of the nose to good on the rearward portion. The local Reynolds numbers of transition based on calculated momentum thickness varied between 1, 600 and 350. Laminar flow was maintained at momentum thickness Reynolds numbers of about 1,000 until the free-stream Reynolds number based on a length of 1 foot reached about 27 X 10(exp 6). At slightly higher free-stream Reynolds numbers transition occurred at momentum thickness Reynolds numbers as low as 250.
Garland, Benjamine J↗
Preliminary results from a free-flight investigation of boundary-layer transition and heat transfer on a highly polished 8-inch-diameter hemisphere-cylinder at Mach numbers up to 3 and Reynolds numbers based on a length of 1 foot up to 17.7 x 10(exp
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Hall, James R↗
Free-flight Determination of Boundary-layer Transition and Heat Transfer for a Hemisphere-cylinder at Mach Numbers to 5.6
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Krasnican, M J↗
Effect of Distributed Granular-type Roughness on Boundary-layer Transition at Supersonic Speeds with and Without Surface Cooling
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Braslow, Albert L↗
Some Experiments at High Supersonic Speeds on the Aerodynamic and Boundary-layer Transition Characteristics of High-drag Bodies of Revolution
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Seiff, Alvin↗
Effects of surface roughness and extreme cooling on boundary-layer transition for 15 degrees cone-cylinder in free flight at Mach numbers to 7.6
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Rabb, Leonard↗