Numerical solution for airfoils near stall in optimized boundary-fitted curvilinear coordinates
Author:
Affiliation:
1. USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio
2. USAF, Acquisition Logistics Div., Wright-Patterson AFB, Ohio
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1978-284
Reference30 articles.
1. Automatic numerical generation of body-fitted curvilinear coordinate system for field containing any number of arbitrary two-dimensional bodies
2. Hodge, J.K., Numerical Solution of Incomprrs___ sible Laminar Flow about Arbitrary Rodics in B o k Fitted Curvilinear Coordinates. Ph.D. Dissertation.Mississippi State University, December 1975.
3. Stone, A.L."A Numerical Solution of the Navier-Stokes Equations for Flow over an Arbitrary Airfoil," M.S. Thesis,Air Force Institute of Tcchnology, Wright-Piltcerson AFB, Ohio: GAElAEl76D-5 (1976).
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1. Numerical Simulation of Near Wakes Utilizing a Relaxation Turbulence Model;AIAA Journal;1980-12
2. Computational Aerodynamics Development and Outlook;AIAA Journal;1979-12
3. Implicit Algorithm for the Conservative Transonic Full-Potential Equation Using an Arbitrary Mesh;AIAA Journal;1979-10
4. An implicit algorithm for the conservative transonic full potential equation using an arbitrary mesh;11th Fluid and PlasmaDynamics Conference;1978-07-10
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