XFOIL Version 6.96 Calculated polar for: FX 84-W-097 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.3487 0.08832 0.08522 -0.0253 1.0000 0.0515 -9.000 -0.3413 0.08489 0.08181 -0.0257 1.0000 0.0528 -8.750 -0.4383 0.08809 0.08484 -0.0300 1.0000 0.0505 -8.500 -0.4276 0.08527 0.08203 -0.0291 1.0000 0.0515 -8.250 -0.4203 0.08237 0.07916 -0.0295 1.0000 0.0528 -8.000 -0.4179 0.07901 0.07585 -0.0313 1.0000 0.0540 -7.750 -0.4195 0.07544 0.07235 -0.0339 1.0000 0.0552 -7.500 -0.4208 0.07116 0.06811 -0.0385 1.0000 0.0567 -7.250 -0.4259 0.06719 0.06418 -0.0417 1.0000 0.0581 -7.000 -0.4305 0.06137 0.05786 -0.0524 0.9897 0.0617 -6.750 -0.4106 0.05357 0.05010 -0.0570 0.9842 0.0635 -6.500 -0.3822 0.05033 0.04685 -0.0599 0.9776 0.0655 -6.250 -0.3510 0.04614 0.04245 -0.0647 0.9710 0.0699 -6.000 -0.3318 0.03343 0.02853 -0.0694 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1.0000 8.750 1.0720 0.02516 0.01702 -0.0290 0.0400 1.0000 9.000 1.0857 0.02631 0.01828 -0.0271 0.0376 1.0000 9.250 1.0996 0.02767 0.01970 -0.0254 0.0352 1.0000 9.500 1.1151 0.02919 0.02126 -0.0241 0.0333 1.0000 9.750 1.1474 0.03277 0.02484 -0.0251 0.0309 1.0000 10.000 1.1608 0.03371 0.02600 -0.0233 0.0298 1.0000 10.250 1.1782 0.03543 0.02794 -0.0221 0.0285 1.0000 10.500 1.1970 0.03778 0.03053 -0.0213 0.0277 1.0000 10.750 1.2119 0.04041 0.03344 -0.0201 0.0272 1.0000 11.000 1.2214 0.04332 0.03666 -0.0184 0.0269 1.0000 11.250 1.2242 0.04648 0.04014 -0.0161 0.0268 1.0000 11.500 1.2210 0.04978 0.04379 -0.0137 0.0270 1.0000 11.750 1.2150 0.05271 0.04698 -0.0116 0.0267 1.0000 12.000 1.2062 0.05587 0.05039 -0.0098 0.0264 1.0000 12.250 1.1930 0.05969 0.05448 -0.0085 0.0266 1.0000 12.500 1.1833 0.06286 0.05783 -0.0079 0.0260 1.0000 12.750 1.1590 0.06840 0.06369 -0.0079 0.0267 1.0000 13.000 1.1369 0.07390 0.06944 -0.0089 0.0271 1.0000 13.250 1.1156 0.07954 0.07529 -0.0108 0.0272 1.0000 13.500 1.0901 0.08652 0.08248 -0.0138 0.0279 1.0000 13.750 1.0658 0.09382 0.08994 -0.0177 0.0282 1.0000 14.000 1.0410 0.10200 0.09827 -0.0225 0.0289 1.0000 14.250 1.0167 0.11104 0.10742 -0.0279 0.0297 1.0000