Download or read book Aerodynamic Heating at Mach 8 of Attached Inflatable Decelerator Configurations written by Theodore R. Jr Creel and published by . This book was released on 1971 with total page 84 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 1974 with total page 792 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 1972 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static Aerodynamic Characteristics Pressure Distributions and RAM air Inflation of Attached Inflatable Decelerator Models at Mach 3 0 written by William D. Deveikis and published by . This book was released on 1970 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static aerodynamic characteristics, pressure distributions, and ram air inflation of attached inflatable drag chute models at supersonic speed.

Download or read book Thermal and Stress Analysis of an Attached Inflatable Decelerator AID Deployed in the Mars and Earth Atmospheres written by and published by . This book was released on 1971 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Deployment and Performance Characteristics of 1 5 meter Supersonic Attached Inflatable Decelerators written by Herman L. Bohon and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Interference Heating on a Swept Cylinder in Region of Intersection with a Wedge at Mach Number 8 written by Dennis M. Bushnell and published by . This book was released on 1965 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Free flight Measurements of Aerodynamic Heat Transfer to Mach Number 3 9 and of Drag to Mach Number 6 9 of a Fin stabilized Cone cylinder Configuration written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.

Download or read book Pressure and Heat Transfer Measurements for Mach 8 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls Heat transfer data for delta wing surface written by Louis G. Kaufman and published by . This book was released on 1964 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Several Ramp fairing Umbilical and Pad Configurations on Aerodynamic Heating to Apollo Command Module at Mach 8 written by James Larry Hunt and published by . This book was released on 1968 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static Aerodynamic Characteristics Pressure Distributions and Ram air Inflation of Attached Inflatable Decelerator Models at Mach 3 0 written by William D. Deveikis and published by . This book was released on 1970 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static Longitudinal Aerodynamic Characteristics of Some Supersonic Decelerator Models at Mach Numbers of 2 30 and 4 63 written by Edwin E. Davenport and published by . This book was released on 1969 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Evaluation of an Infrared Heating Simulation of a Mach 4 63 Flight on an X 15 Horizontal Stabilizer written by Roger A. Fields and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Infrared heating simulation of Mach 4.63 flight on X-15 horizontal stabilizer.

Download or read book A Discussion of Methods for Reducing Aerodynamic Heating in Supersonic Flight written by A. J. Eggers (Jr.) and published by . This book was released on 1955 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aeronautical Engineering written by and published by . This book was released on 1972 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).

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.

Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 850 pages. Available in PDF, EPUB and Kindle. Book excerpt: