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°
Title | 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° PDF eBook |
Author | John O. Reller |
Publisher | |
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.
Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees
Title | Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees PDF eBook |
Author | John O. Jr Reller |
Publisher | |
Pages | 56 |
Release | 1955 |
Genre | |
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Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8
Title | Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8 PDF eBook |
Author | |
Publisher | |
Pages | 0 |
Release | 1957 |
Genre | |
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Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95
Title | Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 PDF eBook |
Author | Jerome D. Julius |
Publisher | |
Pages | 32 |
Release | 1959 |
Genre | Heat |
ISBN |
Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9
Title | Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9 PDF eBook |
Author | |
Publisher | |
Pages | 64 |
Release | 1953 |
Genre | |
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Temperature recovery factors were determined on the cylindrical surface of a number of 40 deg cone cylinder models at zero angle of attack and at M = 2.86. The investigation was performed in a 40- by 40-cm intermittent tunnel and an 18- by 18-cm continous tunnel. With atmospheric tunnel-supply conditions, the turbulent recovery factor was found to be 0.89 + or - 0.5% and independent of Reynolds number in the range of 200,000 to 800,000, with Reynolds number based on wall conditions. The turbulent recovery factor can be represented by the cube root of the Prandtl number for a Prandtl number calculated at wall conditions. In the transitional region of the boundary layer, a maximum recovery factor 0.5 to 1% higher than the turbulent value was obtained. Boundary layer history had a marked effect on the value of the recovery factor. The results were compared with the theoretical and experimental findings of other investigators.
Scientific and Technical Aerospace Reports
Title | Scientific and Technical Aerospace Reports PDF eBook |
Author | |
Publisher | |
Pages | 456 |
Release | 1966 |
Genre | Aeronautics |
ISBN |
A Review of High-speed, Convective, Heat-transfer Computation Methods
Title | A Review of High-speed, Convective, Heat-transfer Computation Methods PDF eBook |
Author | Michael E. Tauber |
Publisher | |
Pages | 44 |
Release | 1989 |
Genre | Aerodynamic heating |
ISBN |