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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4475 0.09085 0.08602 -0.0278 1.0000 0.0289 -9.000 -0.4477 0.08622 0.08145 -0.0306 1.0000 0.0289 -8.750 -0.4347 0.08586 0.08111 -0.0287 1.0000 0.0312 -8.500 -0.4377 0.08104 0.07637 -0.0320 1.0000 0.0309 -8.000 -0.4625 0.06460 0.05997 -0.0471 1.0000 0.0290 -7.250 -0.4794 0.05064 0.04566 -0.0496 0.9993 0.0291 -7.000 -0.4599 0.04418 0.03872 -0.0547 0.9841 0.0292 -6.750 -0.4370 0.03911 0.03316 -0.0582 0.9721 0.0296 -6.500 -0.4119 0.03536 0.02898 -0.0605 0.9612 0.0303 -6.250 -0.3849 0.03244 0.02565 -0.0622 0.9512 0.0315 -6.000 -0.3555 0.03026 0.02308 -0.0637 0.9426 0.0341 -5.750 -0.3295 0.02768 0.01990 -0.0641 0.9321 0.0365 -5.500 -0.3022 0.02542 0.01705 -0.0642 0.9227 0.0379 -5.250 -0.2746 0.02352 0.01493 -0.0645 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0.01536 0.00713 -0.0499 0.5847 1.0000 4.750 0.7804 0.01555 0.00742 -0.0494 0.5727 1.0000 5.000 0.8058 0.01573 0.00768 -0.0489 0.5609 1.0000 5.250 0.8312 0.01592 0.00795 -0.0483 0.5484 1.0000 5.500 0.8562 0.01612 0.00825 -0.0477 0.5346 1.0000 5.750 0.8804 0.01629 0.00850 -0.0469 0.5151 1.0000 6.000 0.9034 0.01643 0.00866 -0.0459 0.4874 1.0000 6.250 0.9253 0.01665 0.00883 -0.0447 0.4533 1.0000 6.500 0.9464 0.01701 0.00915 -0.0436 0.4150 1.0000 6.750 0.9661 0.01752 0.00957 -0.0423 0.3695 1.0000 7.000 0.9831 0.01830 0.01011 -0.0408 0.3099 1.0000 7.250 0.9960 0.01951 0.01092 -0.0391 0.2347 1.0000 7.500 1.0047 0.02119 0.01208 -0.0372 0.1546 1.0000 7.750 1.0135 0.02292 0.01341 -0.0353 0.1001 1.0000 8.000 1.0237 0.02445 0.01479 -0.0334 0.0751 1.0000 8.250 1.0344 0.02585 0.01615 -0.0316 0.0617 1.0000 8.500 1.0445 0.02722 0.01755 -0.0297 0.0527 1.0000 8.750 1.0533 0.02858 0.01902 -0.0276 0.0476 1.0000 9.000 1.0601 0.02992 0.02043 -0.0254 0.0432 1.0000 9.250 1.0644 0.03155 0.02208 -0.0232 0.0397 1.0000 9.500 1.0727 0.03302 0.02370 -0.0214 0.0366 1.0000 9.750 1.0808 0.03464 0.02542 -0.0198 0.0345 1.0000 10.000 1.0889 0.03635 0.02721 -0.0183 0.0327 1.0000 10.250 1.0973 0.03840 0.02924 -0.0170 0.0307 1.0000 10.500 1.1102 0.03999 0.03106 -0.0158 0.0288 1.0000 10.750 1.1223 0.04178 0.03301 -0.0148 0.0270 1.0000 11.000 1.1348 0.04376 0.03514 -0.0137 0.0258 1.0000 11.250 1.1465 0.04587 0.03740 -0.0128 0.0249 1.0000 11.500 1.1570 0.04818 0.03983 -0.0119 0.0240 1.0000 11.750 1.1673 0.05089 0.04267 -0.0111 0.0233 1.0000 12.000 1.1727 0.05404 0.04609 -0.0102 0.0227 1.0000 12.250 1.1718 0.05709 0.04946 -0.0095 0.0222 1.0000 12.500 1.1675 0.06047 0.05318 -0.0090 0.0217 1.0000 12.750 1.1598 0.06418 0.05719 -0.0089 0.0211 1.0000 13.000 1.1506 0.06827 0.06156 -0.0093 0.0206 1.0000 13.250 1.1390 0.07282 0.06638 -0.0102 0.0203 1.0000 13.500 1.1253 0.07784 0.07166 -0.0117 0.0201 1.0000 13.750 1.1089 0.08359 0.07766 -0.0139 0.0201 1.0000 14.000 1.0907 0.08996 0.08426 -0.0169 0.0201 1.0000 14.250 1.0700 0.09721 0.09174 -0.0208 0.0202 1.0000 14.500 1.0480 0.10546 0.10019 -0.0257 0.0204 1.0000 14.750 1.0240 0.11496 0.10988 -0.0318 0.0207 1.0000 15.000 0.9991 0.12590 0.12096 -0.0389 0.0212 1.0000