Reynolds Number, Compressibility, and Leading-Edge Bluntness Effects on Delta-Wing Aerodynamics
An overview of Reynolds number, compressibility, and leading edge bluntness effects is presented for a 65 degree delta wing. The results of this study address both attached and vortex-flow aerodynamics and are based upon a unique data set obtained in the NASA-Langley National Transonic Facility (NTF) for i) Reynolds numbers ranging from conventional wind-tunnel to flight values, ii) Mach numbers ranging from subsonic to transonic speeds, and iii) leading-edge bluntness values that span practical slender wing applications. The data were obtained so as to isolate the subject effects and they present many challenges for Computational Fluid Dynamics (CFD) studies.
A new vortex flow experiment for computer code validation
Abstract : In this paper the present knowledge on the vortex formation on slender delta wings is summarized. The interference mechanisms between primary and secondary vortices as well as the vortex breakdown phenomenon are especially emphasized. The effects of Mach number and Reynolds number are treated separately and the differences in the flow around wings with sharp and rounded leading edges are discussed. The experimental details necessary for the validation of numerical methods are derived and a brief review of relevant modern experimental techniques is given. Finally a configuration suited for a new International Vortex Flow Experiment (VFE-2) as well as a corresponding test program are presented.
Low Speed Wind Tunnel Experiments on a Delta Wing Oscillating in Pitch
Thema sind statische und dynamische Kraft- und Druckmessungen an einem Deltaflugel mit einer Vorderkantenpfeilung von 65&°. im Niedergeschwindigkeitsbereich. Es werden Ergebnisse von erzwungenen Nickschwingungen um verschiedene mittlere Anstellwinkel vorgestellt.