XFOIL Version 6.96 Calculated polar for: FX 78-K-140/20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.2353 0.09118 0.08770 -0.0732 0.7235 0.0040 -10.500 -0.2240 0.08968 0.08621 -0.0748 0.7226 0.0048 -10.250 -0.2392 0.08192 0.07850 -0.0784 0.7219 0.0041 -10.000 -0.2346 0.07891 0.07552 -0.0806 0.7209 0.0044 -9.750 -0.2369 0.07444 0.07109 -0.0835 0.7198 0.0048 -9.500 -0.2444 0.06902 0.06573 -0.0874 0.7188 0.0052 -9.250 -0.2722 0.06053 0.05728 -0.0948 0.7172 0.0046 -8.750 -0.4420 0.03102 0.02680 -0.0837 0.7139 0.0045 -8.500 -0.4596 0.02508 0.02010 -0.0779 0.7128 0.0045 -8.250 -0.4409 0.02432 0.01921 -0.0769 0.7119 0.0048 -8.000 -0.4319 0.02182 0.01626 -0.0741 0.7110 0.0049 -7.750 -0.4044 0.02238 0.01687 -0.0745 0.7102 0.0056 -7.500 -0.3881 0.02084 0.01504 -0.0728 0.7091 0.0059 -7.250 -0.3678 0.01986 0.01383 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0.01094 -0.0565 0.3044 1.0000 7.500 1.0170 0.01891 0.01271 -0.0517 0.2499 1.0000 7.750 0.9987 0.02138 0.01475 -0.0467 0.1747 1.0000 8.000 0.9820 0.02394 0.01683 -0.0423 0.0939 1.0000 8.250 0.9772 0.02591 0.01853 -0.0392 0.0400 1.0000 8.500 0.9790 0.02753 0.01997 -0.0369 0.0117 1.0000 8.750 0.9932 0.02836 0.02084 -0.0360 0.0109 1.0000 9.000 1.0057 0.02937 0.02189 -0.0348 0.0088 1.0000 9.250 1.0167 0.03051 0.02309 -0.0335 0.0070 1.0000 9.500 1.0257 0.03183 0.02446 -0.0321 0.0056 1.0000 9.750 1.0405 0.03271 0.02539 -0.0314 0.0053 1.0000 10.000 1.0529 0.03383 0.02655 -0.0304 0.0045 1.0000 10.250 1.0615 0.03526 0.02808 -0.0291 0.0047 1.0000 10.500 1.0730 0.03646 0.02933 -0.0282 0.0038 1.0000 10.750 1.0758 0.03841 0.03136 -0.0266 0.0032 1.0000 11.000 1.0832 0.04004 0.03307 -0.0253 0.0032 1.0000 11.250 1.0908 0.04168 0.03478 -0.0242 0.0031 1.0000 11.500 1.1023 0.04298 0.03613 -0.0235 0.0033 1.0000 11.750 1.1070 0.04489 0.03814 -0.0222 0.0031 1.0000 12.000 1.1110 0.04693 0.04028 -0.0209 0.0028 1.0000 12.250 1.1197 0.04855 0.04196 -0.0201 0.0029 1.0000 12.500 1.1251 0.05046 0.04395 -0.0191 0.0031 1.0000 12.750 1.1295 0.05251 0.04611 -0.0178 0.0028 1.0000 13.000 1.1366 0.05433 0.04802 -0.0168 0.0027 1.0000 13.250 1.1445 0.05609 0.04986 -0.0160 0.0027 1.0000 13.500 1.1515 0.05794 0.05183 -0.0151 0.0028 1.0000 13.750 1.1560 0.05996 0.05400 -0.0134 0.0026 1.0000 14.000 1.1637 0.06182 0.05597 -0.0125 0.0027 1.0000 14.250 1.1707 0.06379 0.05806 -0.0118 0.0025 1.0000 14.500 1.1772 0.06584 0.06022 -0.0111 0.0027 1.0000 14.750 1.1811 0.06824 0.06280 -0.0100 0.0026 1.0000 15.000 1.1822 0.07111 0.06590 -0.0086 0.0025 1.0000 15.250 1.1831 0.07405 0.06900 -0.0081 0.0025 1.0000 15.500 1.1806 0.07755 0.07272 -0.0075 0.0024 1.0000 15.750 1.1826 0.08034 0.07560 -0.0079 0.0025 1.0000 16.000 1.1852 0.08316 0.07846 -0.0089 0.0021 1.0000 16.250 1.1755 0.08783 0.08340 -0.0084 0.0022 1.0000 16.500 1.1746 0.09127 0.08694 -0.0092 0.0021 1.0000 16.750 1.1495 0.09876 0.09482 -0.0093 0.0023 1.0000 17.000 1.1259 0.10630 0.10264 -0.0106 0.0025 1.0000 17.250 1.1003 0.11468 0.11128 -0.0129 0.0026 1.0000 17.500 1.1385 0.11144 0.10781 -0.0140 0.0020 1.0000 17.750 1.1452 0.11407 0.11042 -0.0159 0.0019 1.0000 18.000 1.0720 0.13237 0.12938 -0.0209 0.0024 1.0000 18.250 1.0419 0.14350 0.14075 -0.0263 0.0024 1.0000