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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1442 0.13020 0.12711 0.0172 1.0000 0.0026 -19.500 -1.1767 0.12018 0.11695 0.0120 1.0000 0.0027 -19.250 -1.2049 0.11114 0.10776 0.0074 1.0000 0.0026 -19.000 -1.2266 0.10354 0.10002 0.0037 1.0000 0.0026 -18.750 -1.2508 0.09566 0.09199 -0.0001 1.0000 0.0026 -18.500 -1.2700 0.08882 0.08502 -0.0034 1.0000 0.0026 -18.250 -1.2848 0.08288 0.07897 -0.0061 1.0000 0.0027 -18.000 -1.2990 0.07712 0.07308 -0.0087 1.0000 0.0026 -17.750 -1.3127 0.07161 0.06747 -0.0111 1.0000 0.0027 -17.500 -1.3175 0.06753 0.06328 -0.0127 1.0000 0.0027 -17.250 -1.3276 0.06278 0.05843 -0.0146 1.0000 0.0027 -17.000 -1.3311 0.05911 0.05467 -0.0160 1.0000 0.0027 -16.750 -1.3389 0.05503 0.05049 -0.0173 1.0000 0.0029 -16.500 -1.3420 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0.5636 3.250 0.3554 0.00847 0.00189 0.0021 0.2145 0.5670 3.500 0.3805 0.00884 0.00209 0.0025 0.1698 0.5705 3.750 0.4072 0.00905 0.00223 0.0027 0.1522 0.5739 4.000 0.4342 0.00922 0.00237 0.0029 0.1407 0.5772 4.250 0.4608 0.00939 0.00252 0.0032 0.1277 0.5816 4.500 0.4875 0.00957 0.00267 0.0034 0.1174 0.5861 4.750 0.5145 0.00972 0.00281 0.0036 0.1103 0.5905 5.000 0.5412 0.00988 0.00298 0.0038 0.1037 0.5952 5.250 0.5682 0.01002 0.00314 0.0040 0.0980 0.6013 5.500 0.5940 0.01027 0.00333 0.0044 0.0823 0.6079 5.750 0.6198 0.01051 0.00354 0.0047 0.0720 0.6160 6.000 0.6459 0.01072 0.00375 0.0050 0.0654 0.6220 6.250 0.6717 0.01093 0.00397 0.0054 0.0598 0.6273 6.500 0.6977 0.01113 0.00418 0.0057 0.0550 0.6319 6.750 0.7229 0.01140 0.00443 0.0061 0.0492 0.6362 7.000 0.7484 0.01160 0.00467 0.0066 0.0474 0.6413 7.250 0.7737 0.01182 0.00492 0.0070 0.0459 0.6471 7.500 0.7985 0.01205 0.00519 0.0075 0.0442 0.6548 8.000 0.8476 0.01254 0.00579 0.0086 0.0416 0.6818 8.250 0.8718 0.01282 0.00612 0.0091 0.0402 0.6948 8.500 0.8956 0.01311 0.00648 0.0098 0.0392 0.7047 8.750 0.9204 0.01331 0.00672 0.0102 0.0384 0.7131 9.000 0.9446 0.01354 0.00700 0.0108 0.0378 0.7218 9.250 0.9685 0.01376 0.00728 0.0114 0.0364 0.7299 9.500 0.9915 0.01402 0.00760 0.0121 0.0349 0.7404 9.750 1.0131 0.01429 0.00795 0.0131 0.0334 0.7551 10.000 1.0331 0.01456 0.00836 0.0143 0.0319 0.8024 10.250 1.0537 0.01494 0.00878 0.0153 0.0303 0.8160 10.500 1.0745 0.01521 0.00914 0.0164 0.0296 0.8306 10.750 1.0934 0.01539 0.00949 0.0179 0.0287 0.8681 11.250 1.1827 0.01641 0.01068 0.0094 0.0219 1.0000 11.500 1.2007 0.01697 0.01121 0.0106 0.0189 1.0000 11.750 1.2182 0.01754 0.01179 0.0118 0.0165 1.0000 12.000 1.2336 0.01820 0.01245 0.0133 0.0139 1.0000 12.250 1.2424 0.01909 0.01332 0.0157 0.0098 1.0000 12.500 1.2509 0.01992 0.01417 0.0180 0.0080 1.0000 12.750 1.2593 0.02090 0.01519 0.0199 0.0066 1.0000 13.000 1.2672 0.02212 0.01646 0.0212 0.0054 1.0000 13.250 1.2789 0.02322 0.01761 0.0218 0.0052 1.0000 13.500 1.2893 0.02456 0.01902 0.0223 0.0047 1.0000 13.750 1.2991 0.02604 0.02056 0.0225 0.0043 1.0000 14.000 1.3076 0.02779 0.02238 0.0224 0.0040 1.0000 14.250 1.3167 0.02950 0.02416 0.0223 0.0039 1.0000 14.500 1.3233 0.03149 0.02622 0.0221 0.0036 1.0000 14.750 1.3315 0.03335 0.02814 0.0219 0.0035 1.0000 15.000 1.3373 0.03549 0.03036 0.0215 0.0035 1.0000 15.250 1.3424 0.03769 0.03263 0.0212 0.0033 1.0000 15.500 1.3449 0.04018 0.03520 0.0207 0.0031 1.0000 15.750 1.3469 0.04276 0.03787 0.0202 0.0031 1.0000 16.000 1.3472 0.04553 0.04072 0.0196 0.0030 1.0000 16.250 1.3468 0.04844 0.04371 0.0189 0.0029 1.0000 16.500 1.3439 0.05169 0.04706 0.0180 0.0029 1.0000 16.750 1.3399 0.05512 0.05058 0.0170 0.0028 1.0000 17.000 1.3363 0.05870 0.05424 0.0158 0.0028 1.0000 17.250 1.3303 0.06270 0.05835 0.0143 0.0028 1.0000 17.500 1.3233 0.06700 0.06275 0.0126 0.0028 1.0000 17.750 1.3131 0.07187 0.06773 0.0106 0.0027 1.0000 18.000 1.3035 0.07678 0.07274 0.0085 0.0027 1.0000 18.250 1.2882 0.08270 0.07878 0.0058 0.0026 1.0000 18.500 1.2740 0.08857 0.08477 0.0031 0.0026 1.0000 18.750 1.2544 0.09547 0.09181 -0.0002 0.0026 1.0000 19.000 1.2363 0.10233 0.09878 -0.0035 0.0026 1.0000 19.250 1.2135 0.11008 0.10667 -0.0073 0.0026 1.0000