XFOIL Version 6.96 Calculated polar for: WORTMANN FX 76-100 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 ------ -------- --------- --------- -------- -------- -------- -13.000 -0.8048 0.08954 0.08394 -0.0191 1.0000 0.0321 -12.750 -0.8316 0.07996 0.07428 -0.0257 1.0000 0.0317 -12.500 -0.8574 0.07158 0.06576 -0.0318 1.0000 0.0313 -12.250 -0.8837 0.06453 0.05850 -0.0367 1.0000 0.0313 -12.000 -0.9034 0.05940 0.05317 -0.0389 1.0000 0.0311 -11.750 -0.9262 0.05495 0.04844 -0.0395 1.0000 0.0315 -11.500 -0.9436 0.05145 0.04466 -0.0382 1.0000 0.0317 -11.250 -0.9573 0.04855 0.04146 -0.0355 1.0000 0.0319 -11.000 -0.9635 0.04596 0.03868 -0.0329 1.0000 0.0326 -10.750 -0.9599 0.04386 0.03650 -0.0311 1.0000 0.0335 -10.500 -0.9552 0.04181 0.03428 -0.0291 1.0000 0.0342 -10.250 -0.9488 0.03977 0.03203 -0.0271 1.0000 0.0352 -10.000 -0.9402 0.03782 0.02984 -0.0252 1.0000 0.0365 -9.750 -0.9299 0.03594 0.02765 -0.0233 1.0000 0.0382 -9.500 -0.9179 0.03422 0.02554 -0.0213 1.0000 0.0402 -9.250 -0.9039 0.03242 0.02372 -0.0199 1.0000 0.0419 -9.000 -0.8883 0.03102 0.02224 -0.0184 1.0000 0.0436 -8.750 -0.8722 0.02972 0.02081 -0.0168 1.0000 0.0460 -8.500 -0.8550 0.02851 0.01934 -0.0152 1.0000 0.0492 -8.250 -0.8387 0.02712 0.01789 -0.0136 1.0000 0.0517 -8.000 -0.8219 0.02602 0.01675 -0.0120 1.0000 0.0547 -7.750 -0.8041 0.02502 0.01563 -0.0105 1.0000 0.0588 -7.500 -0.7871 0.02395 0.01450 -0.0087 1.0000 0.0630 -7.250 -0.7699 0.02302 0.01354 -0.0071 1.0000 0.0675 -7.000 -0.7516 0.02217 0.01256 -0.0054 1.0000 0.0735 -6.750 -0.7346 0.02127 0.01170 -0.0037 1.0000 0.0808 -6.500 -0.7168 0.02044 0.01086 -0.0020 1.0000 0.0897 -6.250 -0.6985 0.01968 0.01012 -0.0004 1.0000 0.1020 -6.000 -0.6801 0.01895 0.00947 0.0012 1.0000 0.1183 -5.750 -0.6611 0.01831 0.00887 0.0027 1.0000 0.1390 -5.500 -0.6419 0.01774 0.00839 0.0042 1.0000 0.1632 -5.250 -0.6223 0.01725 0.00796 0.0056 1.0000 0.1887 -5.000 -0.6024 0.01681 0.00755 0.0071 1.0000 0.2137 -4.750 -0.5827 0.01638 0.00719 0.0085 1.0000 0.2379 -4.500 -0.5627 0.01601 0.00686 0.0099 1.0000 0.2625 -4.250 -0.5430 0.01562 0.00655 0.0114 1.0000 0.2878 -4.000 -0.5234 0.01524 0.00628 0.0129 1.0000 0.3151 -3.750 -0.5038 0.01488 0.00601 0.0145 1.0000 0.3448 -3.500 -0.4843 0.01453 0.00579 0.0160 1.0000 0.3763 -3.250 -0.4648 0.01420 0.00559 0.0176 1.0000 0.4107 -3.000 -0.4454 0.01389 0.00541 0.0192 1.0000 0.4480 -2.750 -0.4261 0.01359 0.00529 0.0209 1.0000 0.4883 -2.500 -0.4066 0.01332 0.00521 0.0225 1.0000 0.5332 -2.250 -0.3868 0.01309 0.00518 0.0242 1.0000 0.5828 -2.000 -0.3662 0.01290 0.00518 0.0258 1.0000 0.6337 -1.750 -0.3432 0.01275 0.00524 0.0270 0.9997 0.6875 -1.500 -0.3007 0.01269 0.00538 0.0244 0.9917 0.7487 -1.250 -0.2568 0.01273 0.00554 0.0216 0.9844 0.8010 -1.000 -0.2102 0.01283 0.00569 0.0182 0.9772 0.8436 -0.750 -0.1596 0.01294 0.00582 0.0141 0.9693 0.8769 -0.500 -0.1071 0.01302 0.00590 0.0095 0.9599 0.9021 -0.250 -0.0543 0.01306 0.00594 0.0049 0.9490 0.9213 0.000 0.0001 0.01308 0.00595 0.0000 0.9368 0.9369 0.250 0.0546 0.01306 0.00594 -0.0050 0.9213 0.9491 0.500 0.1071 0.01302 0.00590 -0.0095 0.9020 0.9599 0.750 0.1596 0.01294 0.00582 -0.0141 0.8770 0.9692 1.000 0.2102 0.01283 0.00569 -0.0182 0.8439 0.9772 1.250 0.2570 0.01273 0.00554 -0.0216 0.8013 0.9845 1.500 0.3008 0.01269 0.00537 -0.0243 0.7474 0.9917 1.750 0.3432 0.01276 0.00524 -0.0270 0.6865 0.9998 2.250 0.3868 0.01309 0.00518 -0.0242 0.5829 1.0000 2.500 0.4066 0.01332 0.00522 -0.0225 0.5337 1.0000 2.750 0.4260 0.01359 0.00529 -0.0208 0.4880 1.0000 3.000 0.4453 0.01389 0.00541 -0.0192 0.4481 1.0000 3.250 0.4648 0.01420 0.00559 -0.0176 0.4107 1.0000 3.500 0.4843 0.01453 0.00579 -0.0160 0.3764 1.0000 3.750 0.5038 0.01488 0.00601 -0.0144 0.3449 1.0000 4.000 0.5234 0.01524 0.00626 -0.0129 0.3157 1.0000 4.250 0.5429 0.01562 0.00655 -0.0114 0.2881 1.0000 4.500 0.5626 0.01601 0.00686 -0.0099 0.2623 1.0000 4.750 0.5826 0.01639 0.00719 -0.0085 0.2377 1.0000 5.000 0.6023 0.01681 0.00756 -0.0070 0.2132 1.0000 5.250 0.6221 0.01725 0.00795 -0.0056 0.1884 1.0000 5.500 0.6419 0.01774 0.00839 -0.0042 0.1632 1.0000 5.750 0.6610 0.01832 0.00887 -0.0027 0.1390 1.0000 6.000 0.6800 0.01895 0.00947 -0.0012 0.1181 1.0000 6.250 0.6984 0.01968 0.01012 0.0004 0.1018 1.0000 6.500 0.7167 0.02044 0.01086 0.0020 0.0895 1.0000 6.750 0.7346 0.02128 0.01171 0.0037 0.0808 1.0000 7.000 0.7515 0.02218 0.01257 0.0054 0.0735 1.0000 7.250 0.7699 0.02303 0.01355 0.0071 0.0674 1.0000 7.500 0.7871 0.02396 0.01450 0.0088 0.0629 1.0000 7.750 0.8041 0.02502 0.01564 0.0105 0.0587 1.0000 8.000 0.8220 0.02601 0.01674 0.0120 0.0546 1.0000 8.250 0.8388 0.02713 0.01790 0.0136 0.0518 1.0000 8.500 0.8551 0.02851 0.01935 0.0152 0.0492 1.0000 8.750 0.8723 0.02973 0.02082 0.0168 0.0461 1.0000 9.000 0.8885 0.03103 0.02225 0.0183 0.0437 1.0000 9.250 0.9040 0.03245 0.02375 0.0199 0.0419 1.0000 9.500 0.9183 0.03429 0.02560 0.0213 0.0403 1.0000 9.750 0.9304 0.03603 0.02773 0.0232 0.0386 1.0000 10.000 0.9404 0.03789 0.02992 0.0252 0.0367 1.0000 10.250 0.9488 0.03984 0.03211 0.0271 0.0353 1.0000 10.500 0.9554 0.04187 0.03436 0.0291 0.0343 1.0000 10.750 0.9605 0.04381 0.03644 0.0310 0.0334 1.0000 11.000 0.9651 0.04580 0.03848 0.0327 0.0325 1.0000 11.250 0.9589 0.04845 0.04135 0.0354 0.0320 1.0000 11.500 0.9429 0.05138 0.04461 0.0381 0.0315 1.0000 11.750 0.9253 0.05491 0.04843 0.0394 0.0312 1.0000 12.000 0.9051 0.05920 0.05297 0.0388 0.0310 1.0000 12.250 0.8814 0.06485 0.05885 0.0361 0.0310 1.0000 12.500 0.8591 0.07145 0.06563 0.0317 0.0313 1.0000 12.750 0.8291 0.08069 0.07504 0.0248 0.0316 1.0000 13.000 0.8001 0.09094 0.08538 0.0176 0.0320 1.0000