Author: J.Leith PotterPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Experience with an Overexpanded Nozzle in a Low-density, Hypervelocity Wind Tunnel
Author: J.Leith PotterAn 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.
NOL Hypervelocity Wind Tunnel
Author: Naval Ordnance Laboratory (White Oak, Md.).Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 70
Book Description
U.S. Government Research Reports
Author: Technical Publications Announcements with Indexes
Author: United States. National Aeronautics and Space AdministrationPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1318
Book Description
Design and Testing of an Axisymmetric Hypersonic Nozzle for a Low Density Wind Tunnel
Author: George J. MaslachInviscid and Viscous Hypersonic Nozzle Flow with Finite Rate Chemical Reactions
Author: E. S. LevinskyPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 54
Book Description
Procedures are developed for determining the inviscid core and boundary layer development in diverging nozzles with high enthalpy reservoir conditions in which the gas composition has been displaced from equilibrium by chemical relaxation. A finite difference procedure, based on the method of characteristics, is used for the inviscid flow with finite rate chemical reactions. Laminar boundary layer profiles, based on local similarity, are obtained by integrating the coupled boundary layer and chemical reaction equations outward from the nozzle wall. Free stream boundary conditions on the chemical specie concentrations and the thermodynamic variables are satisfied by iterating o the unknow concentrations and derivatives at the wall. Numerical calculations are presented for the AEDC, VKF low density tunnel and the Convair hypersonic shock tunnel. Effects of chemical reactions in the boundary layer are restricted to the region in which the core flow has not yet frozen and in which the boundary layer is thin. When the boundary layer is thick enough to influence the core expansion, gas phase reactions are frozen. (Author).
Paper
Author: Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 700
Book Description
Journal of Applied Mechanics
Author: Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 942
Book Description
Publishes original research in all branches of mechanics including aerodynamics; aeroelasticity; boundary layers; computational mechanics; constitutive modeling of materials; dynamics; elasticity; flow and fracture; heat transfer; hydraulics; impact; internal flow; mechanical properties of materials; micromechanics; plasticity; stress analysis; structures; thermodynamics; turbulence; vibration; and wave propagation.
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