Journal ArticleDOI
Shock Tube as a Device for Testing Transonic Airfoils at High Reynolds Numbers
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In this paper, a performance analysis of gas-driven shock tubes is presented, showing that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be generated behind the primary shock in a large shock tube.Abstract:
A performance analysis of gas-driven shock tubes shows that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be generated behind the primary shock in a large shock tube. A study of flow over simple airfoils has been carried out at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photos and airfoil pressure measurements show that steady transonic flows similar to those observed for the airfoils in wind tunnels can be generated within the available testing time in a shock tube with either properly-contoured test section walls or a properly-designed slotted-wall test section. The study indicates that the shock tube is a useful facility for studying two-dimensional high Reynolds number transonic airfoil flows.read more
Citations
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Journal ArticleDOI
Airfoil Flow Visualization and Pressure Measurements in High-Reynolds-Number Transonic Flow
TL;DR: In this article, a shock tube flow is used to generate a high-Reynolds-number transonic flow for aerodynamic testing, achieving a Mach number between 0.6 and 0.9.
Journal ArticleDOI
Over forty years of continuous research at UTIAS on nonstationary flows and shock waves
TL;DR: In this paper, a survey of the literature on non-stationary shock wave, rarefaction wave and contact surfaces can be found, along with a brief survey of some of the most relevant references.
Over forty years of continuous research at UTIAS on nonstationary flows and shock waves
TL;DR: In this article, a survey of the literature on non-stationary shock wave properties and their interaction with the physical world can be found, including the effects of sonic-boom on humans, animals and structures, as well as the properties of planar, cylindrical and spherical shock waves.
Proceedings ArticleDOI
Preliminary Study on Diaphragmless Shock Tube for Transonic Airfoil Testing with PDI
TL;DR: In this article, a diaphragmless shock tube is developed for the transonic and the high-subsonic airfoil testing. And the flow visualization of the shock tube as the wind tunnel is performed by the PDI (point diffraction interferometry) technique.
Proceedings ArticleDOI
A Modified Point-Diffraction Interferometry for Shock Tube Airfoil Testing
TL;DR: In this paper, a modified point diffraction interferometry was developed for shock tube airfoil flows to discuss the effect of Mach number and operation gas, and the results showed that in CO2 modes, the weak kink point of the fringe does not appear in the Mach number 0.6.
References
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Journal ArticleDOI
Calculation of plane steady transonic flows
Earll M. Murman,Julian D. Cole +1 more
TL;DR: In this paper, the transonic small disturbance theory is used to solve for the flow past thin airfoils including cases with imbedded shock waves, and a boundary value problem is formulated for the case of a subsonic freestream Mach number.
Journal ArticleDOI
Analysis of Embedded Shock Waves Calculated by Relaxation Methods
TL;DR: In this paper, the requirements for uniqueness of the calculated jump conditions across embedded shock waves are investigated for type-dependent difference systems used in transonic flow studies, and sufficient conditions are (1) the equations should be differenced in conservative form and (2) a special difference operator should be used when switching from a hyperbolic to an elliptic operator.
Journal ArticleDOI
Shock Tube Test Time Limitation Due to Turbulent-Wall Boundary Layer
TL;DR: In this article, the authors investigated the test time limitation due to the premature arrival of the contact surface of the boundary layer and compared the results with those for wholly laminar-wall boundary layers, and found that, for a given shock Mach number, the maximum possible test time (in a long shock tube) varies as d 6/4p co1/4 and d2p CD for both air and argon.
Journal ArticleDOI
Transonic Flow about a Thick Circular-Arc Airfoil
TL;DR: In this paper, an experimental and theoretical study of transonic flow over a thick airfoil, prompted by a need for adequately documented experiments that could provide rigorous verification of viscous flow simulation computer codes, is reported.
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