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382 Appendix B
3. a = 16 degree angle of attack.
Input file: degl6_Inp.txt
Output file: degl6_0ut.txt
Appendix 6C. Panel Program for Multielement Airfoils
Compile panelm.f (Hess-Smith Panel Method) and generate PC executable file
panelm.exe
Input variable explanations
Geometry of a multielement airfoils for a — 12 degree angle of attack for
Input file: panelm_inp.txt
Output file: panelm_out.txt
Chapter 7
Boundary-Layer Equations
Differential Method with CS Model: Two-Dimensional Flows
Compile blp2d.for (2-dimensional Differential Boundary-Layer Program) and
generate PC executable file blp2d.exe. Click for he u s e r ' s manual.
t
Test Case NACA 0012 Airfoil with a = 4 degree
Input data: blp2dln20.txt
t
Output data: blp2d0u20. x t
Chapter 8
Stability and Transition
n
Transition Prediction with the e -Method
Compile tp2d. f (Stability Program) and generate PC executable file tp2d. exe.
s
s
Test Case NACA 0012 Airfoil at a = 4 degree
Input data: stp2dln3.txt
t
Output data: stp2d0ut. x t
Chapter 9
Grid Generation
9.4 Algebraic and Elliptic Methods (GRID.f)
9.6 Conformal Mapping Methods (Conform.f)
9.6.2 Wind Tunnel Mapping Methods (windtunnel.f)
