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An Extension Of The 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 161
Download An Extension Of The 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 161 full books in PDF, epub, and Kindle. Read online An Extension Of The 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 161 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
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 An Extension of the 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 An Extension of the 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 1954 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results indicate that the trend found previously of an increase in boundary-layer transition Reynolds number with increase in model cooling continued to higher Reynolds numbers. The highest transition Reynolds number obtained with cooling was 28,500,000. At this Reynolds number, the classical Tollmien-Schlichting wave type of boundary-layer number, the instability was apparently overshadowed by surface roughness effects. The results indicated that, when transition was fixed by surface irregularities or airstream flow disturbances, cooling was not effective in obtaining laminar flow behind the irregularity or disturbances.
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 1954 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary investigation has been made of the effects of heat transfer on boundary-layer transition on a body of revolution at a Mach number of 1.61 and over a Reynolds number range of 7,000,000 to 20,000,000, based on body length. The body had a parabolic-arc profile, blunt-base, and a fineness ratio of 12.2 (NACA RM-10). The results indicated that, by cooling the model an average of about 50 degrees F, the Reynolds number for which laminar boundary-layer flow could be maintained over the entire length of the body was increased from the value of 11,500,000 without cooling to over 20,000,000, the limit of the present tests. Heatig the model an average of about 12 degrees F on the other hand decreased the transition Reynolds number from 11,500,000 to about 8,000,000. These effects of heat transfer on transition were considerably larger than previously found in similar investigations in other wind tunnels. It appears that, if the boundary-layer transition Reynolds number for zero heat transfer is large, as in the present experiments, then the sensitivity of transition to heating or cooling is high; if the zero-heat-transfer transition Reynolds number is low, then transition is relatively insensitive to heat-transfer effects.
Book Synopsis An 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 An 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 1955 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1955 with total page 608 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Journal of the Royal Aeronautical Society by :
Download or read book Journal of the Royal Aeronautical Society written by and published by . This book was released on 1954 with total page 910 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Journal of the Royal Aeronautical Society by : Royal Aeronautical Society
Download or read book The Journal of the Royal Aeronautical Society written by Royal Aeronautical Society and published by . This book was released on 1954 with total page 938 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Note on the Effect of Heat Transfer on Peak Pressure Rise Associated with Separation of Turbulent Boundary Layer on a Body of Revolution (NACA RM-10) at a Mach Number of 1.61 by : K. R. Czarnecki
Download or read book A Note on the Effect of Heat Transfer on Peak Pressure Rise Associated with Separation of Turbulent Boundary Layer on a 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 1957 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to determine the effect of heat transfer on the peak pressure rise associated with the separation of a turbulent boundary layer on a body of revolution (NACA RM-10) at a Mach number of 1.61. Tests were made over a Reynolds number range from 11.6 X 10 to the 6th to 34.8 X 10 to the 6th and with 0 to 120 degrees F of cooling, which corresponds to a ratio of model-wall temperature to stagnation temperature of 0.96 (zero heat transfer) to 0.75. The stagnation temperature was approximately 570 degrees F absolute. Boundary-layer separation was induced by means of forward-facing steps or collars at the base of the model and changes in heat transfer were obtained by cooling the model. The peak pressure rise was determined from shock angles measured from schlieren photographs.
Book Synopsis Correlation of Supersonic Convective Heat-transfer Coefficients from Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10) by : Leo T. Chauvin
Download or read book Correlation of Supersonic Convective Heat-transfer Coefficients from Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10) written by Leo T. Chauvin and published by . This book was released on 1951 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat transfer data are presented for a Mach number range of 1.02 to 2.48 and for a Reynolds number range of 3,180,000 to 163,850,000 based on the axial distance from the nose to the point at which temperature measurements were made.
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 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 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 Flight Measurements of Boundary-layer Temperature Profiles on a Body of Revolution (NACA RM-10) at Mach Numbers from 1.2 to 3.5 by : Andrew G. Swanson
Download or read book Flight Measurements of Boundary-layer Temperature Profiles on a Body of Revolution (NACA RM-10) at Mach Numbers from 1.2 to 3.5 written by Andrew G. Swanson and published by . This book was released on 1957 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A fin-stabilized parabolic body of revolution, the NACA RM-10, was flight tested as a rocket-propelled model. Boundary-layer static-temperature profiles were determined from total-temperature measurements made with a series of probes mounted circumferentially around the body near the rear end and from Mach number profiles which were obtained from a total-pressure rake at the same body axial location. These static-temperature profiles showed excellent agreement with temperature profiles computed from the theory of Crocco.
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 Correlation of Supersonic Convection Heat-transfer Coefficients from Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10) by : Leo T. Chauvin
Download or read book Correlation of Supersonic Convection Heat-transfer Coefficients from Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10) written by Leo T. Chauvin and published by . This book was released on 1956 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local coefficients of convective heat transfer have been evaluated from skin temperatures along the body of an NACA research missile designated RM-10. The general shape of the body was a parabola of revolution of fineness ratio 12.2. Heat-transfer data are presented for a Mach number range of 1.02 to 2.48 and for a Reynolds number range of 3,180,000 to 163,850,000 based on the axial distance from the nose to the point at which temperature measurements were made.
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree 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 Degree 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 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Correlation of Supersonic Convective Heat-transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10) by : Langley Aeronautical Laboratory
Download or read book Correlation of Supersonic Convective Heat-transfer Coefficients From Measurements of the Skin Temperature of a Parabolic Body of Revolution (NACA RM-10) written by Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-09 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
