Open Access
Experimental testing at transonic speeds
J. A. Jr. Blackwell
- Vol. 81, pp 189-238
TLDR
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
More filters
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
More filters
Journal ArticleDOI
Systems of conservation laws
Peter D. Lax,Burton Wendroff +1 more
TL;DR: In this article, a wide class of difference equations is described for approximating discontinuous time dependent solutions, with prescribed initial data, of hyperbolic systems of nonlinear conservation laws, and the best ones are determined, i.e., those which have the smallest truncation error and in which the discontinuities are confined to a narrow band of 2-3 meshpoints.
Journal ArticleDOI
Iterative solution of transonic flows over airfoils and wings, including flows at mach 1
TL;DR: In this article, a new method of calculating transonic flows based on a "rotated" difference scheme is described, which is suitable for the calculation of both two and three-dimensional flows without restriction on the speed at infinity and is well adapted to computer use.
BookDOI
Supercritical Wing Sections II
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.