************************************************** VT Aerospace Aircraft Design Software Series ************************************************** Program JKayVLM A program to estimate the subsonic aerodynamics and stability and control derivatives for an assessment of the control power required in conceptual aircraft designs. The basic method is the vortex ring variation of the vlm method. Conceived and written by Jacob Kay. This program modified by - W.H. Mason and Alex Benoliel, March 1993 - W.H. Mason, Nov. 16 1996 - L.T. Leifsson, Feb 2004 The Department of Aerospace and Ocean Engineering, Virginia Tech, Blacksburg, VA 24061 http://www.aoe.vt.edu, email: whmason@vt.edu VLM Based Stability & Control Evaluation Code icase = 3 MACH NUMBER = 0.20000 Sref = 400.00000 c ref = 11.70000 b ref = 36.00000 HEIGHT ABOVE GROUND = 8.00000 X-cg = 32.40000 Z-cg = 1.00000 CL0 = -0.07784 Cm0 = 0.01807 Cdi(at alpha = 0) = 0.00047 CL-alpha = 4.93909 Cm-alpha = -0.40949 Cm/CL = -0.08291 Cdi/CL^2 = 0.06005 CL (at alpha = 5) = 0.35318 Cdi(at alpha = 5) = 0.00749 Lift-curve slope of tail due to downwash of wing = 0.48045 CL-q = 8.88230 CM-q = -5.86074 CL-delta [2 1] = 0.07212 Cm-delta [2 1] = 0.14026 CL-delta [2 2] = 1.15303 Cm-delta [2 2] = 0.12812 CL-delta [3 1] = 0.03362 Cm-delta [3 1] = 0.01560 CL-delta [3 2] = 0.67143 Cm-delta [3 2] = -0.33240 CL-delta [4 1] = 0.94745 Cm-delta [4 1] = -1.13187 Cl-delta [2 1] = -0.00830 Cn-delta [2 1] = -0.00146 Cl-delta [2 2] = -0.17614 Cn-delta [2 2] = -0.00436 Cl-delta [3 1] = -0.00661 Cn-delta [3 1] = -0.00030 Cl-delta [3 2] = -0.17322 Cn-delta [3 2] = -0.00054 Cl-delta [4 1] = -0.10780 Cn-delta [4 1] = 0.02525 Cy-beta = -0.52457 Cn-beta = 0.07900 Cl-beta = -0.10010 Cy-r = 0.46587 Cn-r = -0.18577 Cl-r = 0.08320 Cl-p = -0.43447 Cn-p = -0.11396 Cy-delta [2 2] = 0.10781 Cl-delta [2 2] = 0.02099 Cn-delta [2 2] = -0.04148 Cy-delta [4 2] = 0.10821 Cl-delta [4 2] = 0.02097 Cn-delta [4 2] = -0.04219 Run completed successfully.