Heat Transfer And Pressure Distribution At A Mach Number Of 68 On Bodies With Conical Flares And Extensive Flow Separationbjonh V Becker And Peter F Korycinski PDF Download
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Author | : John V. Becker |
Publisher | : |
Total Pages | : 0 |
Release | : 1962 |
Genre | : Aerodynamic load |
ISBN | : |
Download Heat Transfer and Pressure Distribution at a Mach Number of 6.8 on Bodies with Conical Flares and Extensive Flow Separation.&bJonh V. Becker and Peter F. Korycinski Book in PDF, ePub and Kindle
Author | : Victor Zakkay |
Publisher | : |
Total Pages | : 86 |
Release | : 1962 |
Genre | : Boundary layer |
ISBN | : |
Download Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0 Book in PDF, ePub and Kindle
A modified equation for the heat transfer coefficient in the transitional and fully turbulent region based on the F.P.R.E. method is then presented. This method gives good agreement with the experimental results presented here.
Author | : Davis H. Crawford |
Publisher | : |
Total Pages | : 54 |
Release | : 1961 |
Genre | : Aerodynamic heating |
ISBN | : |
Download The Effect of Air Bleed on the Heat Transfer and Pressure Distribution on 30° Conical Flares at Mach Number of 6.8 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 | : J. David Dearing |
Publisher | : |
Total Pages | : 28 |
Release | : 1969 |
Genre | : Aerodynamic heating |
ISBN | : |
Download Laminar Heat-transfer Distributions for a Blunted-cone, Cone-frustum Reentry Configuration at Mach 10 Book in PDF, ePub and Kindle
Author | : Paul F. Holloway |
Publisher | : |
Total Pages | : 106 |
Release | : 1965 |
Genre | : Aerodynamic heating |
ISBN | : |
Download An Investigation of Heat Transfer Within Regions of Separated Flow at a Mach Number of 6.0 Book in PDF, ePub and Kindle
Author | : Eugene Sevigny |
Publisher | : |
Total Pages | : 50 |
Release | : 1959 |
Genre | : Boundary layer |
ISBN | : |
Download The Effect of Centrifugal Forces on Boundary Layer Transition for a Highly Heated Body Book in PDF, ePub and Kindle
Author | : William D. Deveikis |
Publisher | : |
Total Pages | : 30 |
Release | : 1961 |
Genre | : Fluid mechanics |
ISBN | : |
Download Local Aerodynamic Heat Transfer and Boundary-layer Transition on Roughened Sphere-ellipsoid Bodies at Mach Number 3.0 Book in PDF, ePub and Kindle
Author | : Charles R. Rumsey |
Publisher | : |
Total Pages | : 66 |
Release | : 1961 |
Genre | : Fluid mechanics |
ISBN | : |
Download Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 Book in PDF, ePub and Kindle
Author | : J. Leith Potter |
Publisher | : |
Total Pages | : 26 |
Release | : 1962 |
Genre | : Air flow |
ISBN | : |
Download Experimental Heat Transfer to Blunt Axisymmetric Bodies Near the Limit of Continuum Flow Book in PDF, ePub and Kindle
Measurements of average heat-transfer rates to blunt-nosed, axisymmetric, cold-walled bodies in a low-density, hypervelocity wind tunnel are given. Stream density was such that Reynolds and Knudsen numbers, based on nose radius and conditions immediately behind the bow shock, varied from 5 to 20 and 0.11 to 0.056, respectively. Thus, scaling on the basis of Knudsen number, these conditions may be said to simulate a body of one-foot nose radius at as much as 315,500-ft altitude. Heat-transfer rates are discussed in relation to the flow model successfully used in the past for studies of flows of high Reynolds number. In this context, it was found that measured heat-transfer rates to hemispheres below shock-layer Reynolds numbers of 20 exhibited a decreasing nondimensionalized rate relative to that estimated by methods appropriate to high Reynolds number conditions. This behavior is in accord with various applicable theories. Rates for the flat-faced bodies showed no tendency to decrease, and they were somewhat higher than predicted by theories for high Reynolds numbers.