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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 161
Download 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 161 full books in PDF, epub, and Kindle. Read online 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 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 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 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 1956 with total page 976 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 Handbook of Supersonic Aerodynamics by : D. Adamson
Download or read book Handbook of Supersonic Aerodynamics written by D. Adamson and published by . This book was released on 1961 with total page 366 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Handbook of Supersonic Aerodynamics by : Johns Hopkins University. Applied Physics Laboratory
Download or read book Handbook of Supersonic Aerodynamics written by Johns Hopkins University. Applied Physics Laboratory and published by . This book was released on 1961 with total page 372 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:
Download or read book Research Memorandum written by and published by . This book was released on 1949 with total page 78 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 : 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 Heat Transfer and Skin Friction for Turbulent Boundary Layers on Heated Or Cooled Surfaces at High Speeds by : Coleman duP. Donaldson
Download or read book Heat Transfer and Skin Friction for Turbulent Boundary Layers on Heated Or Cooled Surfaces at High Speeds written by Coleman duP. Donaldson and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The method presented in NACA TN 2692 for evaluating the skin friction of a turbulent boundary layer in compressible flow on an insulated surface is extended to evaluate the turbulent skin friction and heat transfer in compressible flow on a surface which is heated or cooled. The results of this analysis are in good agreement with the heat transfers measured in flight on the NACA RM-10 missile up to Mach number of 3.8.
Book Synopsis Heat Transfer to Blunt Nose Shapes with Laminar Boundary Layers at High Supersonic Speeds by : John O. Reller (Jr.)
Download or read book Heat Transfer to Blunt Nose Shapes with Laminar Boundary Layers at High Supersonic Speeds written by John O. Reller (Jr.) and published by . This book was released on 1957 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Free-flight Measurements of Heat Transfer and Transition on a 10° Cone Having a Low Temperature Ratio by : Charles F. Merlet
Download or read book Supersonic Free-flight Measurements of Heat Transfer and Transition on a 10° Cone Having a Low Temperature Ratio written by Charles F. Merlet and published by . This book was released on 1961 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer coefficients in the form of Stanton number and boundary-layer transition data were obtained from a free-flight test of a 100-inch-long 10° total-angle cone with a 1/16-inch tip radius which penetrated deep into the region of infinite stability of laminar boundary layer over a range of wall-to-local-stream temperature radius and for local Mach numbers from 1.8 to 3.5. Experimental heat-transfer coefficients, obtained at Reynolds numbers up to 160 x 106, were in general somewhat higher than theoretical values. A maximum Reynolds number of transition of only 33 x 106 was obtained. Contrary to theoretical and some other experimental investigations, the transition Reynolds number initially increased while the wall temperature ratio increased at relatively constant Mach number. Further increases in wall temperature ratio were accompanied by a decrease in transition Reynolds number. Increasing transition Reynolds number with increasing Mach number was also indicated at a relatively constant wall temperature ratio.
Book Synopsis Free-flight Investigation of Heat Transfer to an Unswept Cylinder Subjected to an Incident Shock and Flow Interference from an Upstream Body at Mach Numbers Up to 5.50 by : Howard S. Carter
Download or read book Free-flight Investigation of Heat Transfer to an Unswept Cylinder Subjected to an Incident Shock and Flow Interference from an Upstream Body at Mach Numbers Up to 5.50 written by Howard S. Carter and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 106 to 1.87 x 106. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.
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 Survey of Boundary Layer Heat Transfer at High Velocities and High Temperatures by : Ernst Rudolf Georg Eckert
Download or read book Survey of Boundary Layer Heat Transfer at High Velocities and High Temperatures written by Ernst Rudolf Georg Eckert and published by . This book was released on 1960 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Study of Effects of Turbulence Promoters on Heat Transfer by : Armour Research Foundation (U.S.)
Download or read book Study of Effects of Turbulence Promoters on Heat Transfer written by Armour Research Foundation (U.S.) and published by . This book was released on 1950 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report is the summary of a literature survey and analytical study performed by the Armour Research Foundation for NEPA on the subject of the effect of turbulence promotion on forced convection heat transfer and fluid friction.
Book Synopsis 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° by : Raul Jorge Conti
Download or read book 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° written by Raul Jorge Conti and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
