Download or read book Low density Hypervelocity Wind Tunnel Diffuser Performance written by Mancil W. Milligan and published by . This book was released on 1963 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An experimental study of diffusers in an open jet low density hypersonic wind tunnel written by David E. Boylan and published by . This book was released on 1964 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of supersonic diffuser performance in a flow regime in which viscous and compressibility influences are equally important was conducted. The investigation involved Mach numbers from 6 to 16.5. It is shown that, although diffuser recovery compared to higher density regimes is small, using the proper diffuser allowed the required wind tunnel exhaust pressure to be up to 35 times the pressure existing in the test chamber. While this may not seem exceptional at first glance, it is important to note that this was achieved in conjunction with Reynolds numbers on the order of 10 to the minus 3 power below those typical of tunnels yielding higher recoveries. (Author).
Download or read book NASA Technical Note written by and published by . This book was released on 1965 with total page 478 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 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experience with an Overexpanded Nozzle in a Low density Hypervelocity Wind Tunnel written by J.Leith Potter and published by . This book was released on 1962 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book U S Government Research Reports written by and published by . This book was released on 1964 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section written by Rudolf Hermann and published by . This book was released on 1950 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Download or read book Keywords Index to U S Government Technical Reports written by and published by . This book was released on 1962 with total page 1160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Description and Initial Calibration of the Langley 12 inch Hypersonic Ceramic heated Tunnel written by Louis E. Clark 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 Design and Calibration of an Arc heated Hypersonic Low density Wind Tunnel written by Ruth N. Weitmann 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 Proceedings written by and published by . This book was released on 1965 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Guide to Annual Subject Index for Technical Publications Announcements Apr Dec 1962 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 720 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Publications Announcements with Indexes written by United States. National Aeronautics and Space Administration and published by . This book was released on 1962 with total page 1012 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Further Experiments on Impact pressure Probes in a Low density Hypervelocity Flow written by A. B. Bailey and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the behavior of flat-faced, impact-pressure probes with a range of orificeto-probe diameter ratios was made in heated A under conditions where free stream Mach. = 4 to 14, gas temperature = 2700 to 4300 K, and Reynolds number (based on outside probe diameter and conditions behind a normal shock)/in. = 30 to 430. At the lower Reynolds numbers the measured impact pressure was found to decrease with the pressure sensing orifice size. This result agrees with that found in heated N. As the Reynolds number increased this orifice effect became less significant, and at the higher Reynolds numbers no decrease in measured impact pressure was noted for the smallest orifice tested. This tends to confirm the assumption made in some experiments on impact-pressure probes in a low-density hypervelocity flow (AD-268 391) that this behavior is caused by a thermomolecular flow effect. Because this effect is a function solely of pressure at a particular temperature, the greater the pressure the smaller the effect. When Re2 times the square root of density in free stream over density in normal shock is less than 800 in A the measured impact pressure was less than the true impact pressure and decreased to a minimum value, approximately 93% of the true value. As the Reynolds number decreased still further, the viscous effects became dominant, and there was a sharp increase in the measured impact pressure. (Author).s
Download or read book Advanced Experimental Techniques for Study of Hypervelocity Flight written by and published by . This book was released on 1965 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Wind Tunnel Diffuser Performance with High Model Blockage at Moderate to Low Reynolds Numbers written by G. J. Hanus and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Paper written by and published by . This book was released on 1969 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
