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 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.
Book ChapterDOI
The aerodynamic design of section shapes for swept wings
TL;DR: In this paper, the aerodynamic design of section shapes for swept wings is discussed and a method for predicting pressure distributions with shock waves is proposed based on the subsonic distribution.
Journal ArticleDOI
The flow over a wedge profile at mach number one
TL;DR: In this article, the transonic law of similarity was used to compute the flow over a wedge-shaped profile at zero angle of attack and with a free stream Mach number of one.
Journal ArticleDOI
Computation of Separated Transonic Turbulent Flows
TL;DR: In this article, four different algebraic eddy viscoisity models are tested for viability to achieve turbulence closure for the class of flows considered, ranging from an unmodified boundary-layer mixing-length model to a relaxation model incorporating special considerations for the separation bubble region.