Recovery Temperature Transition And Heat Transfer Measurements At Mach 5
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Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution
Author | : Raul Jorge Conti |
Publisher | : |
Total Pages | : 32 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution
Author | : Raul J. Conti |
Publisher | : |
Total Pages | : 36 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45°
Author | : John O. Reller |
Publisher | : |
Total Pages | : 64 |
Release | : 1955 |
Genre | : Aerodynamics |
ISBN | : |
Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.
Effects of Mach Number and Wall-temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5
Author | : Thorval Tendeland |
Publisher | : |
Total Pages | : 24 |
Release | : 1959 |
Genre | : Aerodynamic heating |
ISBN | : |
Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration
Author | : Charles B. Rumsey |
Publisher | : |
Total Pages | : 26 |
Release | : 1955 |
Genre | : Aerodynamic heating |
ISBN | : |
Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
Precision Measurement and Calibration: Temperature
Author | : United States. National Bureau of Standards |
Publisher | : |
Total Pages | : 536 |
Release | : 1969 |
Genre | : Calibration |
ISBN | : |