Accession Number : ADA189871
Title : High Reynolds Number, Low Mach Number, Steady Flow Field Calculations over a NACA 0012 Airfoil Using Navier-Stokes and Interactive Boundary Layer Theory.
Descriptive Note : Master's thesis,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Personal Author(s) : Cowles, Lisa J
PDF Url : ADA189871
Report Date : Dec 1987
Pagination or Media Count : 118
Abstract : A Navier-Stokes code, developed by N.L. Sankar, and an Interactive Boundary Layer code, developed by Tuncer Cebeci, are implemented for high Reynolds number, low Mach flows over a NACA 0012 airfoil. Upper surface pressure distribution, coefficients of lift, coefficients of friction, and velocity profiles obtained from the Navier-Stokes code are compared to results obtained from the Cebeci Interactive Boundary Layer code for steady flow. The steady state cases investigated are at .3 Mach and Reynolds numbers of 1 to 5 million and at .12 Mach and a Reynolds number of 1.5 million. Keywords: Navier Stokes, Interactive boundary layer theory, Lift coefficient, Velocity profiles.
Descriptors : *NAVIER STOKES EQUATIONS, *AIRFOILS, BOUNDARY LAYER, CODING, COEFFICIENTS, FLOW FIELDS, FRICTION, HIGH RATE, INTERACTIONS, MACH NUMBER, PRESSURE DISTRIBUTION, PROFILES, REYNOLDS NUMBER, STEADY FLOW, STEADY STATE, THEORY, VELOCITY, THESES, AERODYNAMIC LIFT
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE