Author: Ruth N. WeitmannPublisher:
ISBN:
Category : Chemistry, Physical and theoretical
Languages : en
Pages : 36
Book Description
Design and Calibration of an Arc-heated, Hypersonic, Low-density Wind Tunnel
Author: Ruth N. WeitmannPublisher:
ISBN:
Category : Chemistry, Physical and theoretical
Languages : en
Pages : 36
Book Description
Description and Preliminary Calibration Tests of a Small Arc-heated Hypersonic Wind Tunnel
Author: William B. BoatrightPublisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 44
Book Description
Low-density Hypervelocity Wind Tunnel Diffuser Performance
Author: Mancil W. MilliganPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 56
Book Description
NASA Technical Note
Author: An Analysis of Initial Static Pressure Probe Measurements in a Low-density Hypervelocity Wind Tunnel
Author: David E. BoylanPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 22
Book Description
An initial experimental program was previously conducted to study the problems in using static pressure probes for flow calibration purposes in low- density, hypervelocity wind tunnels with continuous flow. This data is reviewed in the light of more recent data on thermal transpiration. Results indicate that such probes may be used for what might be termed secondary calibrations, but care is required in interpreting the results. The present experiment yielded data which are compared to static pressures calculated from impact- pressure probe calibrations.
U.S. Government Research Reports
Author: Description and Initial Calibration of the Langley 12-inch Hypersonic Ceramic-heated Tunnel
Author: Louis E. ClarkPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 60
Book Description
Technical Abstract Bulletin
Author: Further Experiments on Impact-pressure Probes in a Low-density, Hypervelocity Flow
Author: A. B. BaileyPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 36
Book Description
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
Astronautical Research 1971
Author: L.G. NapolitanoPublisher: Springer Science & Business Media
ISBN: 9401025592
Category : Technology & Engineering
Languages : en
Pages : 561
Book Description
The International Astronautical Federation is the only professional society in the field of aerospace engineering and Sciences which brings together specialists of all countries interested in the exploration and peaceful exploitation of space. At its annual Congresses a large number of invited and/or carefully selected con tributed papers are presented which cover a wide variety of topics and are distributed over a number of sessions, each one being organized by two leading scientists who later chair the session itself. Each year the selection of specific topics to be dealt with. is dictated either by significant new progress achieved in some sectors or by new developments and trends which are liable to influence substantially the objectives toward which space research and/or application of space technology will be oriented in the immediate future. A second rigorous screening, performed with the help of the Session Chairmen and carried out according to the same criteria identifies finally the papers which are published in the Proceedings. The outcome of all this is reliable and authoritative information as to the actual status and future trends of space activities, both from the research point of view and from the point of view of u~ilization and/or application.