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 |
Measurements of Pressure and Local Heat Transfer on a 20 Deg Cone at Angles of Attack Up to 20 Deg for a Mach Number of 4.95
Title | Measurements of Pressure and Local Heat Transfer on a 20 Deg Cone at Angles of Attack Up to 20 Deg for a Mach Number of 4.95 PDF eBook |
Author | |
Publisher | |
Pages | 32 |
Release | 1959 |
Genre | |
ISBN |
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 | |
Release | 1959 |
Genre | |
ISBN |
Measurements of Pressure and Local Heat Transfer on a 20 Degree Cone at Angles of Attack Up to 20 Degrees for a Mach Number of 4.95
Title | Measurements of Pressure and Local Heat Transfer on a 20 Degree Cone at Angles of Attack Up to 20 Degrees for a Mach Number of 4.95 PDF eBook |
Author | Jerome D. Julius |
Publisher | |
Pages | 28 |
Release | 1959 |
Genre | |
ISBN |
Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90°
Title | Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° PDF eBook |
Author | Raul Jorge Conti |
Publisher | |
Pages | 38 |
Release | 1961 |
Genre | Heat |
ISBN |
Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
Heat-transfer and Pressure Measurements on a Concove-nose Cylinder for a Mach Number Range of 2.49 to 4.44
Title | Heat-transfer and Pressure Measurements on a Concove-nose Cylinder for a Mach Number Range of 2.49 to 4.44 PDF eBook |
Author | Stallings, Jr. (Robert L.) |
Publisher | |
Pages | 21 |
Release | 1959 |
Genre | Aerodynamic measurements |
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
Title | 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 PDF eBook |
Author | Charles B. Rumsey |
Publisher | |
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.