Author: Paul F. BrinichPublisher:
ISBN:
Category :
Languages : en
Pages : 56
Book Description
Recovery Temperature Transition and Heat-transfer Measurements at Mach 5
Author: Paul F. BrinichRecovery Temperature, Transition, and Heat-transfer Measurements at Mach 5
Author: Paul F. BrinichNASA Technical Note
Author: 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 ContiPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
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. ContiPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Book Description
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. RellerPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 64
Book Description
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.
Precision Measurement and Calibration: Temperature
Author: United States. National Bureau of StandardsPublisher:
ISBN:
Category : Calibration
Languages : en
Pages : 536
Book Description
Measurements of heat transfer and recovery temperature in regions of separated flow at a Mach number of 1. 8
Author: Helmut ThomannIndex of NASA Technical Publications
Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Book Description
Effects of Mach Number and Wall-temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5
Author: Thorval TendelandPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 24
Book Description