XFOIL Version 6.96 Calculated polar for: FX LIII-142 K 25 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -0.7142 0.18196 0.17817 0.0345 1.0000 0.0470 -16.500 -0.9370 0.11121 0.10740 -0.0022 1.0000 0.0363 -16.000 -1.0729 0.07802 0.07316 -0.0211 1.0000 0.0311 -15.750 -1.0643 0.07634 0.07161 -0.0222 1.0000 0.0332 -15.500 -1.0749 0.07165 0.06680 -0.0245 1.0000 0.0346 -15.250 -1.0831 0.06769 0.06271 -0.0268 1.0000 0.0361 -15.000 -1.0971 0.06306 0.05786 -0.0289 1.0000 0.0375 -14.750 -1.1072 0.05946 0.05405 -0.0307 1.0000 0.0386 -14.500 -1.1226 0.05455 0.04893 -0.0316 1.0000 0.0403 -14.250 -1.1196 0.05239 0.04681 -0.0320 1.0000 0.0422 -14.000 -1.1182 0.05040 0.04479 -0.0326 1.0000 0.0442 -13.750 -1.1207 0.04810 0.04235 -0.0329 1.0000 0.0462 -13.500 -1.1237 0.04564 0.03969 -0.0329 1.0000 0.0477 -13.250 -1.1288 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0.7874 0.5346 -3.750 -0.4058 0.01273 0.00607 -0.0049 0.7754 0.5471 -3.500 -0.3794 0.01281 0.00607 -0.0043 0.7658 0.5577 -3.250 -0.3529 0.01290 0.00609 -0.0037 0.7572 0.5678 -3.000 -0.3265 0.01299 0.00608 -0.0032 0.7484 0.5782 -2.750 -0.2993 0.01312 0.00614 -0.0028 0.7411 0.5866 -2.500 -0.2723 0.01319 0.00620 -0.0025 0.7328 0.5954 -2.250 -0.2458 0.01335 0.00623 -0.0021 0.7261 0.6059 -2.000 -0.2185 0.01338 0.00633 -0.0017 0.7184 0.6141 -1.750 -0.1917 0.01344 0.00632 -0.0014 0.7121 0.6232 -1.500 -0.1646 0.01346 0.00636 -0.0011 0.7058 0.6317 -1.250 -0.1373 0.01343 0.00632 -0.0009 0.6995 0.6385 -1.000 -0.1098 0.01346 0.00632 -0.0007 0.6940 0.6450 -0.750 -0.0825 0.01341 0.00629 -0.0006 0.6872 0.6515 -0.500 -0.0549 0.01342 0.00630 -0.0003 0.6816 0.6570 -0.250 -0.0276 0.01342 0.00627 -0.0002 0.6751 0.6637 0.000 0.0000 0.01339 0.00627 0.0000 0.6687 0.6687 0.250 0.0276 0.01342 0.00627 0.0002 0.6637 0.6751 0.500 0.0549 0.01342 0.00629 0.0003 0.6570 0.6816 0.750 0.0825 0.01341 0.00629 0.0006 0.6515 0.6872 1.000 0.1098 0.01346 0.00632 0.0007 0.6450 0.6940 1.250 0.1373 0.01343 0.00632 0.0009 0.6385 0.6995 1.500 0.1646 0.01346 0.00636 0.0011 0.6317 0.7058 1.750 0.1917 0.01344 0.00632 0.0014 0.6233 0.7121 2.000 0.2185 0.01337 0.00632 0.0018 0.6138 0.7183 2.250 0.2458 0.01335 0.00622 0.0021 0.6057 0.7260 2.500 0.2723 0.01319 0.00619 0.0025 0.5953 0.7328 2.750 0.2993 0.01312 0.00614 0.0028 0.5865 0.7411 3.000 0.3265 0.01299 0.00609 0.0032 0.5782 0.7485 3.250 0.3529 0.01290 0.00608 0.0037 0.5678 0.7572 3.500 0.3794 0.01281 0.00607 0.0043 0.5575 0.7659 3.750 0.4058 0.01273 0.00605 0.0050 0.5469 0.7754 4.000 0.4317 0.01264 0.00608 0.0056 0.5349 0.7874 4.250 0.4576 0.01253 0.00604 0.0062 0.5223 0.8015 4.500 0.4832 0.01240 0.00598 0.0069 0.5090 0.8163 4.750 0.5087 0.01229 0.00597 0.0077 0.4948 0.8324 5.000 0.5344 0.01218 0.00601 0.0084 0.4795 0.8514 5.250 0.5618 0.01205 0.00605 0.0088 0.4611 0.8758 5.500 0.5951 0.01196 0.00605 0.0080 0.4370 0.9050 5.750 0.6360 0.01206 0.00613 0.0054 0.3999 0.9401 6.000 0.6833 0.01246 0.00637 0.0011 0.3401 0.9722 6.250 0.7229 0.01330 0.00681 -0.0024 0.2658 1.0000 6.500 0.7373 0.01405 0.00728 -0.0007 0.2234 1.0000 6.750 0.7540 0.01482 0.00782 0.0008 0.1910 1.0000 7.000 0.7714 0.01561 0.00846 0.0021 0.1664 1.0000 7.250 0.7874 0.01656 0.00925 0.0037 0.1458 1.0000 7.500 0.8047 0.01741 0.01002 0.0051 0.1276 1.0000 7.750 0.8209 0.01837 0.01085 0.0066 0.1148 1.0000 8.000 0.8406 0.01903 0.01155 0.0077 0.1060 1.0000 8.250 0.8566 0.02007 0.01248 0.0092 0.0998 1.0000 8.500 0.8768 0.02073 0.01323 0.0103 0.0953 1.0000 8.750 0.8958 0.02145 0.01397 0.0115 0.0911 1.0000 9.000 0.9131 0.02250 0.01493 0.0127 0.0874 1.0000 9.250 0.9325 0.02334 0.01585 0.0138 0.0846 1.0000 9.500 0.9520 0.02419 0.01677 0.0149 0.0821 1.0000 9.750 0.9712 0.02508 0.01771 0.0159 0.0796 1.0000 10.000 0.9903 0.02603 0.01868 0.0169 0.0775 1.0000 10.250 1.0105 0.02742 0.02005 0.0176 0.0748 1.0000 10.500 1.0301 0.02890 0.02166 0.0184 0.0728 1.0000 10.750 1.0471 0.02994 0.02286 0.0195 0.0710 1.0000 11.000 1.0643 0.03120 0.02427 0.0206 0.0692 1.0000 11.250 1.0789 0.03237 0.02557 0.0219 0.0670 1.0000 11.500 1.0919 0.03334 0.02658 0.0232 0.0646 1.0000 12.000 1.1092 0.03647 0.02987 0.0263 0.0594 1.0000 12.250 1.1112 0.03748 0.03107 0.0286 0.0575 1.0000 12.500 1.1138 0.03844 0.03214 0.0301 0.0552 1.0000 12.750 1.1187 0.03975 0.03352 0.0312 0.0533 1.0000 13.000 1.1262 0.04097 0.03471 0.0318 0.0512 1.0000 13.250 1.1289 0.04379 0.03763 0.0325 0.0490 1.0000 13.500 1.1245 0.04575 0.03981 0.0329 0.0477 1.0000 13.750 1.1214 0.04803 0.04228 0.0328 0.0460 1.0000 14.000 1.1192 0.05034 0.04471 0.0324 0.0441 1.0000 14.250 1.1200 0.05254 0.04698 0.0319 0.0424 1.0000 14.500 1.1239 0.05452 0.04890 0.0315 0.0403 1.0000 14.750 1.1087 0.05956 0.05414 0.0307 0.0387 1.0000 15.000 1.0965 0.06340 0.05821 0.0288 0.0376 1.0000 15.250 1.0841 0.06774 0.06276 0.0266 0.0363 1.0000 15.500 1.0731 0.07218 0.06737 0.0243 0.0350 1.0000 15.750 1.0639 0.07662 0.07192 0.0219 0.0334 1.0000 16.000 1.0736 0.07812 0.07326 0.0209 0.0311 1.0000 16.250 1.0611 0.08348 0.07872 0.0186 0.0303 1.0000 16.500 1.0346 0.09165 0.08712 0.0139 0.0297 1.0000 16.750 1.0108 0.09992 0.09562 0.0090 0.0295 1.0000 17.000 0.9801 0.11003 0.10593 0.0030 0.0297 1.0000 17.250 0.9429 0.12219 0.11828 -0.0044 0.0300 1.0000