Computational study of blowing on delta wings at high alpha
Author:
Affiliation:
1. Stanford University, Stanford, California 94305
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.46424
Reference26 articles.
1. Control of vortical lift on delta wings by tangential leading-edge blowing
2. Numerical study of the effect of tangential leading edge blowing on delta wing vortical flow
3. An investigation of asymmetric vortical flows over delta wings with tangential leading-edge blowing at high angles of attack
4. Control of asymmetric vortical flows over delta wings at high anglesof attack
5. Improved calculations of leading-edge separation from slender, thin, delta wings
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1. Drag Reduction and Turbulent Characteristics of a Low Aspect Ratio Wing with Fluidic On-Demand Winglet;SAE International Journal of Aerospace;2022-04-20
2. Vortical flows over a LEX-delta wing at high angles of attack;KSME International Journal;2004-12
3. Vortical flows over a delta wing at high angles of attack;KSME International Journal;2004-06
4. Optimisation of structured grid spacing parameters for separated flow simulation using mathematical optimisation;Journal of Wind Engineering and Industrial Aerodynamics;1999-04
5. Turbulence models for the computation of flow past airplanes;Progress in Aerospace Sciences;1997-01
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