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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Beschreibung
Zusammenfassung:	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 drag behavior of a NACA 0012 airfoil. Numerical solutions are obtained for a Mach number of 0.3 and a Reynolds number of one million. The parameters examined are angle of attack, fan ejection angle and suction velocity. The numerical code used is based on the Beam-Warming implicit factorization algorithm for solving the two- dimensional mass-averaged compressible Navier-Stokes equations for viscous, unsteady flows. Keywords: Drag reduction, Lift augmentation, Computational fluid dynamics, Mass transfer, Vectored blowing, Theses.