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.
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary layer Transition on a 150 Cone in Free Flight at Supersonic Mach Numbers Up to 5 2 written by Charles B. Rumsey and published by . This book was released on 1961 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract:
Download or read book Aerodynamic Heating and Boundary layer Transition on a 1 10 power Nose Shape in Free Flight at Mach Numbers Up to 6 7 and Free stream Reynolds Numbers Up to 16 X 10 6 written by Benjamine J. Garland and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Measurement of Aerodynamic Heat Transfer to a Deflected Trailing edge Flap on a Delta Fin in Free Flight at Mach Numbers from 1 5 to 2 6 written by Leo T. Chauvin and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone cylinder flare Configuration in Free Flight at Mach Numbers Up to 4 7 written by Charles R. Rumsey and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free flight Skin temperature and Surface pressure Measurements on a Highly Polished Nose Having a 1000 Total angle Cone and a 100 Half angle Conical Flare Section Up to a Mach Number of 4 08 written by Bernard Rashis and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1964 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design studies of hypersonic lifting vehicles have generally indicated that aerodynamic heating may be reduced by using highly swept configurations with blunted leading edges. For laminar boundary layers the effect of sweep angle A on the heat transfer at the leading edge is usually taken as cos A as shown by the data of Feller (ref. 1) who measured the average heat transfer on the front half of a swept cylinder. More recent data (refs. 2 and 3) have indicated that the effect of sweep may be more nearly cos3/2 Lambda which, at a sweep angle of 75 deg, would result in a 50-percent reduction of the heat transfer predicted by the cos A variation. The data and theory of reference 4 also indicate a cos3/2 lambda variation but the theories of references 5 and 6 indicate a variation somewhere between cos A and cos3/2 lambda for large stream Mach numbers. The data of reference 7, in contrast to the investigations just cited, showed large increases in average heat transfer to a circular leading edge with increasing A up to a lambda of about 40 deg. These increases in heat transfer were probably caused by transition to turbulent flow which apparently resulted primarily from the inherent instability of the three-dimensional boundary layer flow on a yawed cylinder. The leading-edge Reynolds numbers of reference 7 were considerably larger than the values in references 1 to 4 and were also larger than typical values for full-scale leading edges of hypersonic vehicles; hence, the main application of the high Reynolds number tests will probably be to bodies at angle of attack.
Download or read book NASA Technical Paper written by United States. National Aeronautics and Space Administration and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Report written by and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1957 with total page 860 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Local Heat Transfer to Blunt Noses at High Supersonic Speeds written by William E. Stoney and published by . This book was released on 1957 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A New Dimension Wallops Island Flight Test Range written by Joseph Adams Shortal and published by . This book was released on 1978 with total page 796 pages. Available in PDF, EPUB and Kindle. Book excerpt:
