Add to ORKGBoundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimensional) and Van Driest (two-dimensional), respectively
Schlieren, recovery temperature, and heat-transfer measurements were made on a hollow cylinder and a...
A highly polished 15 degree included-angle cone-cylinder with hemispherical tip has been flown to ob...
Large bluntness cones with smooth nosetips and roughened frusta were flown in the NASA Ames hyperson...
Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained ...
Heat-transfer coefficients in the form of Stanton number and boundary-layer transition data were obt...
A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-an...
Measurements of aerodynamic heat transfer have been made at several stations on the 15 deg total-ang...
Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt an...
Boundary-layer-transition and heat-transfer measurements were\ud obtained from flight tests of blunt...
The laminar boundary layer on a cooled 20 cone was investigated at Mach numbers of 1.5 and 2.0 to de...
Boundary layer transition measurements were made in flight on a 10 deg transition cone tested previo...
Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959...
Measurements of the location of boundary-layer transition and the local heat transfer have been made...
Laminar, transitional, and turbulent heat-transfer data were measured during a reentry flight at a M...
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semia...
Schlieren, recovery temperature, and heat-transfer measurements were made on a hollow cylinder and a...
A highly polished 15 degree included-angle cone-cylinder with hemispherical tip has been flown to ob...
Large bluntness cones with smooth nosetips and roughened frusta were flown in the NASA Ames hyperson...
Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained ...
Heat-transfer coefficients in the form of Stanton number and boundary-layer transition data were obt...
A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-an...
Measurements of aerodynamic heat transfer have been made at several stations on the 15 deg total-ang...
Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt an...
Boundary-layer-transition and heat-transfer measurements were\ud obtained from flight tests of blunt...
The laminar boundary layer on a cooled 20 cone was investigated at Mach numbers of 1.5 and 2.0 to de...
Boundary layer transition measurements were made in flight on a 10 deg transition cone tested previo...
Two HTV-1 Hypersonic Test Vehicles, Rounds A-40 and A-41, were flown at Holloman AFB in October 1959...
Measurements of the location of boundary-layer transition and the local heat transfer have been made...
Laminar, transitional, and turbulent heat-transfer data were measured during a reentry flight at a M...
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semia...
Schlieren, recovery temperature, and heat-transfer measurements were made on a hollow cylinder and a...
A highly polished 15 degree included-angle cone-cylinder with hemispherical tip has been flown to ob...
Large bluntness cones with smooth nosetips and roughened frusta were flown in the NASA Ames hyperson...