Download or read book Heat transfer and Pressure Distributions at Mach Numbers of 6 0 and 9 6 Over Two Reentry Configurations for the Five stage Scout Vehicle written by Paul F. Holloway and published by . This book was released on 1963 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Corner Radius on Stagnation point Velocity Gradients on Blunt Axisymmetric Bodies written by Ernest V. Zoby and published by . This book was released on 1965 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Note written by United States. National Aeronautics and Space Administration and published by . This book was released on 1963 with total page 480 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book 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 1964 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Keywords Index to U S Government Technical Reports permuted Title Index written by United States. Department of Commerce. Office of Technical Services and published by . This book was released on 1963 with total page 618 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Keywords Index to U S Government Technical Reports written by United States. Department of Commerce. Office of Technical Services and published by . This book was released on 1962 with total page 990 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Journal of the British Interplanetary Society written by British Interplanetary Society and published by . This book was released on 1934 with total page 660 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Corner Radius on Stagnation point Velocity Gradients on Blunt Axisymmetric Bodies written by and published by . This book was released on 1965 with total page 28 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 A Selected Listing of Nasa Scientific and Technical Reports for 1963 written by and published by . This book was released on 1964 with total page 254 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Laminar Heat transfer Distributions for a Blunted cone Cone frustum Reentry Configuration at Mach 10 written by J. David Dearing and published by . This book was released on 1969 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Journal of the Royal Aeronautical Society written by and published by . This book was released on 1962 with total page 962 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Journal of the Royal Aeronautical Society written by Royal Aeronautical Society and published by . This book was released on 1962 with total page 1164 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 1969 with total page 1508 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

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 Measurements of the Surface Flows Heat Transfer Pressure Distribution and Longitudinal Stability of a Mercury Capsule Model at Mach Numbers of 6 9 and 9 6 written by Philip E. Everhart and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: