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:
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.
Download or read book Local Heat Transfer and Recovery Temperatures on Yawed Cylinder at Mach Number of 4 15 and High Reynolds Numbers with List of References written by and published by . This book was released on 1959 with total page 6 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 Local Heat Transfer and Recovery Temperatures on Yawed Cylinder at Mach Numbers of 4 15 and High Reynolds Numbers with List of References written by and published by . This book was released on 1962 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High speed Aircraft written by Robert D. Quinn and published by . This book was released on 2000 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a method that can calculate transient aerodynamic heating and transient surface temperatures at supersonic and hypersonic speeds. This method can rapidly calculate temperature and heating rate time-histories for complete flight trajectories. Semi-empirical theories are used to calculate laminar and turbulent heat transfer coefficients and a procedure for estimating boundary-layer transition is included. Results from this method are compared with flight data from the X-15 research vehicle, YF-12 airplane, and the Space Shuttle Orbiter. These comparisons show that the calculated values are in good agreement with the measured flight data.
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 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.
Download or read book Space Shuttle Aerothermodynamics Technology Conference Held at Ames Research Center Moffett Field Calif December 15 16 1971 written by and published by . This book was released on 1972 with total page 470 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 1970 with total page 434 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Space Scientists and Engineers Selected Biographical and Bibliographical Listing written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reports and Memoranda written by Aeronautical Research Council (Great Britain) and published by . This book was released on 1969 with total page 510 pages. Available in PDF, EPUB and Kindle. Book excerpt: Beginning with no. 650 each hundredth number contains a list of the Reports and memoranda published since the last list.
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 1959 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Prediction of Aerodynamic Heating of Fins on Re entry Vehicles written by E. C. Lemmon and published by . This book was released on 1971 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Evaluation of Active Cooling Systems for a Mach 6 Hypersonic Transport Airframe written by R. G. Helenbrook and published by . This book was released on 1971 with total page 924 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transpiration and convective cooling concepts are examined for the fuselage and tail surface of a Mach 6 hypersonic transport aircraft. Hydrogen, helium, and water are considered as coolants. Heat shields and radiation barriers are examined to reduce heat flow to the cooled structures. The weight and insulation requirements for the cryogenic fuel tanks are examined so that realistic totals can be estimated for the complete fuselage and tail. Structural temperatures are varied to allow comparison of aluminum alloy, titanium alloy, and superalloy construction materials. The results of the study are combined with results obtained on the wing structure, obtained in a previous study, to estimate weights for the complete airframe. The concepts are compared among themselves, and with the uncooled concept on the basis of structural weight, cooling system weight, and coolant weight.
Download or read book Pressure Measurements on Sharp and Blunt 5 Degreee and 15 Degree half angle Cones at Mach Number 3 86 and Angles of Attack to 100 Degrees written by James L. Amick and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Heat transfer Distributions on a Blunt Lifting Body at Mach 3 71 written by Robert L. Stallings and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: The composite body consisted of a spherical nose segment, a delta-slab upper surface with blunt leading edges, wedge sides, and a conical lower surface. The tests were conducted both with and without roughness on the model for a range of angle of attack up to 400. Included is a complete tabulation of the experimental heatii rates and a discussion of the more significant findings.
