Open Access
Experimental testing at transonic speeds
J. A. Jr. Blackwell
- Vol. 81, pp 189-238
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In this paper, the authors defined the normal force and pitch moment coefficients of a wing span and its chord, and the slope of a section normal force vs angle-of-a attack curve.Abstract:
Nomenclature b = wing span c = wing chord c , = section drag coefficient d c = section lift coefficient c = section normal force coefficient n c = slope of section normal force vs angle-ofa attack curve c = section pitching moment coefficient C = aircraft drag coefficient C = aircraft lift coefficient LI C = pressure coefficient Cju = blowing coefficient M = Mach number P = total pressure q , q = freestream dynamic pressureread more
Citations
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Journal ArticleDOI
Advances in the computation of transonic separated flows over finite wings
Unver Kaynak,Jolen Flores +1 more
TL;DR: In this article, the transonic flow around a low-aspect-ratio infinite wing in a wind tunnel is investigated by means of numerical simulations, with a focus on shock-induced separated flows.
Investigation of sidewall boundary layer removal effects on two different chord airfoil models in the Langley 0.3-meter Transonic Cryogenic Tunnel
TL;DR: In this article, an investigation was carried out on two CAST 10-2 airfoil models with chords of 3 in. and 6 in. The tests were conducted in the Langley 0.3m Transonic Cryogenic Tunnel two-dimensional test section equipped with an upstream sidewall boundary layer removal system.
Improvement of subsonic wall corrections in an industrial wind tunnel
TL;DR: This revision of the model representation is based on high fidelity free-air CFD solutions for the NASA Common Research Model, validated by experimental data sets obtained from a semispan version of the CRM tested at the NRC 5ft Trisonic Wind Tunnel.
A Simplified Fourwall Interference Assessment Procedure for Airfoil Data Obtained in the Langley 0.3-Meter Transonic Cryogenic Tunnel
TL;DR: In this paper, a simplified fourwall interference assessment method has been described, and a computer program developed to facilitate correction of the airfoil data obtained in the Langley 0.3m Transonic Cryogenic Tunnel (TCT).
References
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Journal ArticleDOI
Transonic flow about lifting configurations.
TL;DR: In this paper, a transonic flow solution for configurations with span-to-length ratios of order one is presented, where the angles of attack are sufficiently large to produce lift effects that are either dominant or comparable to the thickness effects.
Journal ArticleDOI
Aerodynamics of Slender Bodies and Wing-Body Combinations at M= 1
ReportDOI
On the flow over a cone-cylinder body at mach number one
TL;DR: In this paper, the transonic similarity law proposed by von Karman and Oswatitsch and Berndt based upon slender body theory can be extended to cover cone-cylinder bodies of practical slenderness ratios.
The U.S. 2.5-Meter Cryogenic High Reynolds Number Tunnel
R. R. Howell,L. W. Mckinney +1 more
TL;DR: The U.S. 2.5-Meter Cryogenic High Reynolds Number Tunnel (CHRN) as discussed by the authors is a fan-driven transonic wind tunnel scheduled for operation in 1981.
Journal ArticleDOI
Application of the Thin-Wing-Expansion Method to the Flow of a Compressible Fluid past a Symmetrical Circular Arc Aerofoil
TL;DR: In this paper, the thin-wing expansion method is applied to the flow of a compressible fluid past a symmetrical circular aerofoil and analytical expressions for the velocity potential and the velocity distribution over its surface are obtained.