Author: Mancil W. MilliganPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 56
Book Description
Low-density Hypervelocity Wind Tunnel Diffuser Performance
Author: Mancil W. MilliganPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 56
Book Description
An experimental study of diffusers in an open-jet, low-density, hypersonic wind tunnel
Author: David E. BoylanPublisher:
ISBN:
Category : Diffusers
Languages : en
Pages : 72
Book Description
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).
NASA Technical Note
Author: Scientific and Technical Aerospace Reports
Author: Experience with an Overexpanded Nozzle in a Low-density, Hypervelocity Wind Tunnel
Author: J.Leith PotterU.S. Government Research Reports
Author: Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section
Author: Rudolf HermannPublisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 90
Book Description
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.
Keywords Index to U.S. Government Technical Reports
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1160
Book Description
Keywords Index to U.S. Government Technical Reports (permuted Title Index).
Author: United States. Department of Commerce. Office of Technical ServicesPublisher:
ISBN:
Category : Government publications
Languages : en
Pages : 836
Book Description
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