Navier-Stokes Solution for a NACA 0012 Airfoil with Mass Flux (Fan)

STOL aircraft use a variety of mechanisms to augment lift. Small fans with vectored exhaust imbedded in an aircraft wing could increase lift and reduce drag. The aim of this thesis is to investigate the two-dimensional effect of a small 'fan in wing' on the flow field and on the lift and d...

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Bibliographische Detailangaben
1. Verfasser:	Boyles, Paul D
Format:	Report
Sprache:	eng
Schlagworte:	AERODYNAMIC DRAG AERODYNAMIC LIFT Aerodynamics AIRFOILS ALGORITHMS ANGLE OF ATTACK ANGLES AUGMENTATION BEAM WARMING ALGORITHM BLOWING BOUNDARY LAYER CONTROL CODING COMPRESSIBLE FLOW COMPUTATIONAL FLUID DYNAMICS COMPUTATIONS DRAG REDUCTION EJECTION EMBEDDING FACTOR ANALYSIS FAN IN WING FANS FLOW FIELDS FLUID DYNAMICS FLUX(RATE) LIFT AUGMENTATION MASS FLOW MASS TRANSFER NACA-0012 AIRFOIL NAVIER STOKES EQUATIONS NUMERICAL ANALYSIS REYNOLDS NUMBER SHORT TAKEOFF AIRCRAFT SOLUTIONS(GENERAL) SUBSONIC CHARACTERISTICS SUCTION THESES TWO DIMENSIONAL UNSTEADY FLOW V/STOL VELOCITY VERTICAL BLOWING VERTICAL ORIENTATION VISCOUS FLOW WINGS
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