Download or read book An Experimental Investigation of Boundary layer Transition on a 10 half angle Cone at Mach 6 9 written by Michael C. Fischer and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary layer transition on nose cones at hypersonic speeds.
Download or read book An Experimental Investigation of Boundary layer Transition on a 10 Degree Half angle Cone at Mach 6 9 written by Michael C. Fischer and published by . This book was released on 1970 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Boundary layer Transition on a 10 Half angle Cone at Mach 6 9 written by Michael C. Fischer and published by . This book was released on 1970 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Boundary layer Transition on a Cooled 7 5 Total angle Cone at Mach 10 written by Philip E. Everhart and published by . This book was released on 1967 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Boundary layer Transition on a Cooled 7 5 Degrees Total angle Cone at Mach 10 written by Philip E. Everhart and published by . This book was released on 1967 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Boundary Layer Transition on a Cone at Angle of Attack written by A. Martellucci and published by . This book was released on 1969 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: As the first part of the Strategic Re-entry Technology (STREET G) task to determine the effect of asymmetric transition on static stability, an experimental investigation of the influence of angle of attack on boundary layer transition from location and shape has been conducted at AEDC Tunnel B at Mach 8. The model was a stainless steel 7.2 deg half-angle cone with three bluntness ratios. For each of the bluntness ratios, heat transfer data were obtained for four values of the free stream Reynolds number and for four angles of attack, that is, alpha = 0 deg, 1 deg, 2 deg, and 4 deg. Comparisons of the heat transfer at alpha = o deg were made with theory and good agreement resulted.
Download or read book NASA Technical Note written by and published by . This book was released on 1970 with total page 1004 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation on Unit Reynolds Number and Bluntness Effects on Boundary layer Transition for a 10 Half angle Cone at M infinity written by Michael Carlton Fischer and published by . This book was released on 1969 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 828 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Manned Operations for the Apollo Lunar Module in a Simulated Space Environment written by O. L. Pearson and published by . This book was released on 1970 with total page 920 pages. Available in PDF, EPUB and Kindle. Book excerpt: Simulated space environment performance tests of Apollo lunar module in thermal vacuum environment.
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 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 Scientific and Technical Aerospace Reports written by and published by . This book was released on 1991 with total page 1460 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Download or read book Boundary layer Transition on Cones Near Mach One in an Aeroballistic Range written by J. Leith Potter and published by . This book was released on 1975 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 = or
Download or read book A Selected Listing of NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1970 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Unit Reynolds Number Nose Bluntness Angle of Attack and Roughness on Transition on a 5 Half angle Cone at Mach 8 written by P. Calvin Stainback and published by . This book was released on 1969 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 35th Aerospace Sciences Meeting Exhibit written by and published by . This book was released on 1997 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt:
