Measurements Of Pressure And Local Heat Transfer On A 20 Cone At Angles Of Attack Up To 20 For A Mach Number Of 495
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Author | : Jerome D. Julius |
Publisher | : |
Total Pages | : 32 |
Release | : 1959 |
Genre | : Heat |
ISBN | : |
Download 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 Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 32 |
Release | : 1959 |
Genre | : |
ISBN | : |
Download 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 Book in PDF, Epub and Kindle
Author | : Jerome D. Julius |
Publisher | : |
Total Pages | : |
Release | : 1959 |
Genre | : |
ISBN | : |
Download 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 Book in PDF, Epub and Kindle
Author | : Jerome D. Julius |
Publisher | : |
Total Pages | : 28 |
Release | : 1959 |
Genre | : |
ISBN | : |
Download 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 Book in PDF, Epub and Kindle
Author | : Raul Jorge Conti |
Publisher | : |
Total Pages | : 38 |
Release | : 1961 |
Genre | : Heat |
ISBN | : |
Download 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° Book in PDF, Epub and Kindle
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.
Author | : Stallings, Jr. (Robert L.) |
Publisher | : |
Total Pages | : 21 |
Release | : 1959 |
Genre | : Aerodynamic measurements |
ISBN | : |
Download Heat-transfer and Pressure Measurements on a Concove-nose Cylinder for a Mach Number Range of 2.49 to 4.44 Book in PDF, Epub and Kindle
Author | : John O. Reller |
Publisher | : |
Total Pages | : 64 |
Release | : 1955 |
Genre | : Aerodynamics |
ISBN | : |
Download 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° Book in PDF, Epub and Kindle
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.
Author | : Dennis M. Bushnell |
Publisher | : |
Total Pages | : 40 |
Release | : 1968 |
Genre | : Aerodynamics |
ISBN | : |
Download Heat-transfer and Pressure Distributions on Spherically Blunted 25 ̊half-angle Cone at Mach 8 and Angles of Attack Up to 90 ̊ Book in PDF, Epub and Kindle
Author | : Charles B. Rumsey |
Publisher | : |
Total Pages | : 26 |
Release | : 1955 |
Genre | : Aerodynamic heating |
ISBN | : |
Download 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 Book in PDF, Epub and Kindle
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.
Author | : Charles B. Rumsey |
Publisher | : |
Total Pages | : 42 |
Release | : 1956 |
Genre | : Aerodynamics |
ISBN | : |
Download Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 Book in PDF, Epub and Kindle
Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.