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Heat Transfer And Recovery Temperatures On A Sphere With Laminar Transitional And Turbulent Boundary Layers At Mach Numbers Of 200 And 415
Download Heat Transfer And Recovery Temperatures On A Sphere With Laminar Transitional And Turbulent Boundary Layers At Mach Numbers Of 200 And 415 full books in PDF, epub, and Kindle. Read online Heat Transfer And Recovery Temperatures On A Sphere With Laminar Transitional And Turbulent Boundary Layers At Mach Numbers Of 200 And 415 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Heat Transfer and Recovery Temperatures on a Sphere with Laminar, Transitional, and Turbulent Boundary Layers at Mach Numbers of 2.00 and 4.15 by : Ivan E. Beckwith
Download or read book Heat Transfer and Recovery Temperatures on a Sphere with Laminar, Transitional, and Turbulent Boundary Layers at Mach Numbers of 2.00 and 4.15 written by Ivan E. Beckwith and published by . This book was released on 1957 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made of the pressure and equilibrium-temperature distributions on sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic best transfer was also measured on a sphere at a Mach number of 2.00 and on a hemisphere-cylinder at a Mach number of 4.15. The Reynolds number range for these tests was from 1.5 x 10 to the 6th power to 8.1 x 10 to the 6th power, based on free-stream conditions and the diameter of the spheres.
Book Synopsis Local Aerodynamic Heat Transfer and Boundary-layer Transition on Roughened Sphere-ellipsoid Bodies at Mach Number 3.0 by : William D. Deveikis
Download or read book Local Aerodynamic Heat Transfer and Boundary-layer Transition on Roughened Sphere-ellipsoid Bodies at Mach Number 3.0 written by William D. Deveikis and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers by : Ivan E. Beckwith
Download or read book Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers written by Ivan E. Beckwith and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Influence of Low Wall Temperature on Boundary-layer Transition and Local Heat Transfer on 2-inch-diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 106 by : Morton Cooper
Download or read book The Influence of Low Wall Temperature on Boundary-layer Transition and Local Heat Transfer on 2-inch-diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 106 written by Morton Cooper and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulent-boundary-layer Heat-transfer and Transition Measurements with Surface Cooling at Mach 6 by : Aubrey M. Cary
Download or read book Turbulent-boundary-layer Heat-transfer and Transition Measurements with Surface Cooling at Mach 6 written by Aubrey M. Cary and published by . This book was released on 1970 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0 by : Victor Zakkay
Download or read book Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0 written by Victor Zakkay and published by . This book was released on 1962 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 written by Charles B. Rumsey and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis 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° by : John O. Reller
Download or read book 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° written by John O. Reller and published by . This book was released on 1955 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Measurements of Aerodynamic Heat Transfer in Turbulent Separated Regions at a Mach Number of 1.8 by : Benjamine J. Garland
Download or read book Measurements of Aerodynamic Heat Transfer in Turbulent Separated Regions at a Mach Number of 1.8 written by Benjamine J. Garland and published by . This book was released on 1958 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers by : Ivan E. Beckwith
Download or read book Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers written by Ivan E. Beckwith and published by . This book was released on 1961 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local heat transfer, equilibrium temperatures, and pressure have been measured on a circular cylinder for yaw angles from 0° to 60° and Reynolds numbers from 1X106 to 4X106. Increasing the yaw angle from 0° to 40° generally caused large increases in local heat-transfer coefficients followed by a decrease as the yaw angle was increased to 60°. The level of heating rates and the type if chordwise distribution indicated that a flow mechanism different from the conventional transitional boundary layer may exist for the intermediate yaw angles.
Book Synopsis Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution by : Raul Jorge Conti
Download or read book Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution written by Raul Jorge Conti and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 by : James R. Hall
Download or read book Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 written by James R. Hall and published by . This book was released on 1957 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Local Aerodynamic Heat Transfer and Boundary-layer Transition on Roughened Sphere-ellipsoid Bodies at Mach Number 3.0 by : William D. Deveikis
Download or read book Local Aerodynamic Heat Transfer and Boundary-layer Transition on Roughened Sphere-ellipsoid Bodies at Mach Number 3.0 written by William D. Deveikis and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental heating rates and pressure distributions obtained from aerodynamic heating tests on four steel sphere-ellipsoid bodies with surface roughnesses of 5, 100, and 200 microinches are presented. Free- tream Reynolds numbers based on model spherical diameter, were 4.25 x 10 to the 6th power and 2.76 x 10 to the 6th power, and the stagnation temperature was 650 F. The tests showed that the combination of surface roughness and boundary-layer cooling tend d to promo e arly ra sition and nullify the advantages attributable to the blunt shape of the model for reducing local temperatures. (Author).
Book Synopsis Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution by : Raul J. Conti
Download or read book Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution written by Raul J. Conti and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Preliminary Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61 by : K. R. Czarnecki
Download or read book Preliminary Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61 written by K. R. Czarnecki and published by . This book was released on 1952 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Charles B. Rumsey
Download or read book 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 written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
