XFOIL Version 6.96 Calculated polar for: FX 38-153 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.6069 0.09130 0.08805 -0.0463 1.0001 0.0464 -9.500 -0.6326 0.08753 0.08425 -0.0450 1.0001 0.0463 -9.250 -0.6595 0.08441 0.08109 -0.0426 1.0001 0.0462 -9.000 -0.6873 0.08193 0.07857 -0.0388 1.0001 0.0460 -8.750 -0.7161 0.07987 0.07647 -0.0342 1.0001 0.0458 -8.500 -0.7453 0.07704 0.07346 -0.0303 1.0001 0.0463 -8.250 -0.7847 0.07536 0.07126 -0.0247 1.0001 0.0473 -6.000 -0.6496 0.03747 0.03045 -0.0226 0.9785 0.0307 -5.750 -0.6147 0.03483 0.02744 -0.0240 0.9732 0.0297 -5.500 -0.5698 0.03287 0.02509 -0.0270 0.9696 0.0291 -5.250 -0.5427 0.03090 0.02267 -0.0259 0.9626 0.0271 -5.000 -0.5093 0.02996 0.02157 -0.0267 0.9588 0.0267 -4.750 -0.4733 0.02895 0.02052 -0.0282 0.9562 0.0267 -4.500 -0.4465 0.02797 0.01957 -0.0281 0.9516 0.0269 -4.250 -0.4227 0.02702 0.01866 -0.0279 0.9468 0.0276 -4.000 -0.3888 0.02636 0.01804 -0.0297 0.9433 0.0289 -3.750 -0.3475 0.02592 0.01755 -0.0329 0.9407 0.0315 -3.500 -0.3231 0.02521 0.01682 -0.0329 0.9336 0.0356 -3.250 -0.2846 0.02403 0.01591 -0.0360 0.9298 0.0847 -3.000 -0.2437 0.02156 0.01645 -0.0408 0.9288 0.6751 -2.750 -0.2087 0.02259 0.01743 -0.0413 0.9255 0.7392 -2.500 -0.2017 0.02341 0.01825 -0.0360 0.9171 0.7594 -2.250 -0.1826 0.02463 0.01943 -0.0323 0.9119 0.7780 -2.000 -0.1660 0.02532 0.02006 -0.0289 0.9046 0.7898 -1.750 -0.1431 0.02591 0.02057 -0.0269 0.8983 0.8023 -1.500 -0.1176 0.02684 0.02145 -0.0243 0.8950 0.8170 -1.250 -0.1176 0.02719 0.02181 -0.0174 0.8850 0.8247 -1.000 -0.0867 0.02745 0.02198 -0.0172 0.8814 0.8349 -0.750 -0.0708 0.02767 0.02217 -0.0142 0.8735 0.8456 -0.500 -0.0515 0.02782 0.02228 -0.0107 0.8682 0.8561 -0.250 -0.0213 0.02791 0.02231 -0.0098 0.8656 0.8678 0.000 -0.0065 0.02789 0.02226 -0.0080 0.8562 0.8775 0.250 0.0248 0.02754 0.02187 -0.0078 0.8527 0.8818 0.500 0.0665 0.02719 0.02146 -0.0103 0.8506 0.8849 0.750 0.0817 0.02695 0.02119 -0.0086 0.8401 0.8902 1.000 0.1196 0.02655 0.02075 -0.0108 0.8373 0.8933 1.250 0.1590 0.02609 0.02026 -0.0128 0.8356 0.8953 1.500 0.1730 0.02580 0.01997 -0.0106 0.8245 0.8984 1.750 0.2152 0.02520 0.01935 -0.0133 0.8221 0.9001 2.000 0.2363 0.02487 0.01903 -0.0124 0.8123 0.9033 2.250 0.2765 0.02426 0.01842 -0.0149 0.8088 0.9053 2.500 0.3208 0.02355 0.01771 -0.0180 0.8066 0.9068 2.750 0.3376 0.02304 0.01722 -0.0157 0.7960 0.9095 3.000 0.3780 0.02210 0.01631 -0.0176 0.7930 0.9115 3.250 0.4174 0.02112 0.01535 -0.0192 0.7892 0.9131 3.500 0.4426 0.02049 0.01475 -0.0186 0.7792 0.9155 3.750 0.4859 0.01950 0.01379 -0.0211 0.7762 0.9169 4.000 0.5089 0.01911 0.01345 -0.0205 0.7640 0.9186 4.250 0.5407 0.01857 0.01295 -0.0213 0.7535 0.9199 4.500 0.5821 0.01779 0.01220 -0.0237 0.7432 0.9210 4.750 0.6109 0.01718 0.01161 -0.0236 0.7254 0.9226 5.000 0.6442 0.01662 0.01104 -0.0244 0.7038 0.9240 5.250 0.6810 0.01617 0.01051 -0.0259 0.6768 0.9249 5.500 0.7141 0.01594 0.01013 -0.0268 0.6391 0.9259 5.750 0.7374 0.01600 0.00998 -0.0262 0.5964 0.9274 6.000 0.7539 0.01624 0.01002 -0.0244 0.5553 0.9295 6.250 0.7701 0.01654 0.01018 -0.0228 0.5205 0.9315 6.500 0.7877 0.01690 0.01043 -0.0215 0.4894 0.9330 6.750 0.8051 0.01733 0.01075 -0.0204 0.4589 0.9344 7.000 0.8191 0.01771 0.01103 -0.0186 0.4275 0.9363 7.250 0.8313 0.01814 0.01134 -0.0164 0.3970 0.9381 7.500 0.8456 0.01862 0.01173 -0.0148 0.3642 0.9395 7.750 0.8595 0.01920 0.01218 -0.0132 0.3341 0.9410 8.000 0.8748 0.01979 0.01268 -0.0120 0.3028 0.9426 8.250 0.8902 0.02042 0.01322 -0.0108 0.2761 0.9445 8.500 0.9075 0.02106 0.01379 -0.0100 0.2500 0.9461 8.750 0.9244 0.02181 0.01444 -0.0093 0.2283 0.9473 9.000 0.9434 0.02250 0.01512 -0.0090 0.2092 0.9484 9.250 0.9605 0.02308 0.01570 -0.0081 0.1927 0.9496 9.500 0.9758 0.02373 0.01633 -0.0070 0.1793 0.9510 9.750 0.9915 0.02443 0.01703 -0.0061 0.1668 0.9525 10.000 1.0095 0.02503 0.01771 -0.0054 0.1539 0.9540 10.250 1.0253 0.02575 0.01845 -0.0046 0.1409 0.9560 10.500 1.0408 0.02657 0.01929 -0.0038 0.1284 0.9579 10.750 1.0571 0.02743 0.02019 -0.0032 0.1144 0.9594 11.000 1.0720 0.02844 0.02121 -0.0025 0.0994 0.9607 11.250 1.0825 0.02967 0.02239 -0.0013 0.0850 0.9621 11.500 1.0917 0.03092 0.02365 0.0002 0.0692 0.9637 11.750 1.0961 0.03259 0.02523 0.0020 0.0593 0.9654 12.000 1.1028 0.03418 0.02693 0.0034 0.0531 0.9671 12.250 1.1028 0.03636 0.02912 0.0053 0.0492 0.9688 12.500 1.1126 0.03784 0.03075 0.0063 0.0466 0.9709 12.750 1.1215 0.03944 0.03248 0.0072 0.0444 0.9730 13.000 1.1284 0.04103 0.03415 0.0083 0.0426 0.9754 13.250 1.1336 0.04288 0.03606 0.0092 0.0411 0.9777 13.500 1.1390 0.04487 0.03811 0.0101 0.0397 0.9799 13.750 1.1483 0.04657 0.03997 0.0105 0.0385 0.9823 14.000 1.1565 0.04840 0.04195 0.0108 0.0371 0.9849 14.250 1.1637 0.05034 0.04399 0.0109 0.0358 0.9881 14.500 1.1694 0.05243 0.04616 0.0110 0.0347 0.9924 14.750 1.1738 0.05457 0.04837 0.0112 0.0337 0.9999 15.000 1.1820 0.05688 0.05074 0.0115 0.0327 0.9999 15.250 1.1900 0.05929 0.05331 0.0112 0.0323 0.9999 15.500 1.1966 0.06189 0.05611 0.0108 0.0319 0.9999 15.750 1.2015 0.06474 0.05917 0.0103 0.0313 0.9999 16.000 1.2043 0.06784 0.06247 0.0096 0.0307 0.9999 16.250 1.2053 0.07122 0.06604 0.0086 0.0300 0.9999 16.500 1.2047 0.07485 0.06984 0.0072 0.0291 0.9999 16.750 1.2045 0.07849 0.07360 0.0056 0.0281 0.9999 17.000 1.2052 0.08201 0.07717 0.0041 0.0271 0.9999 17.500 1.1932 0.09122 0.08673 0.0006 0.0257 0.9999 17.750 1.1834 0.09686 0.09262 -0.0026 0.0253 0.9999 18.000 1.1726 0.10289 0.09890 -0.0062 0.0248 0.9999 18.250 1.1613 0.10918 0.10542 -0.0101 0.0243 0.9999 18.500 1.1489 0.11583 0.11228 -0.0144 0.0238 0.9999 18.750 1.1352 0.12296 0.11963 -0.0190 0.0236 0.9999 19.000 1.1201 0.13069 0.12756 -0.0243 0.0233 0.9999 19.250 1.0999 0.13984 0.13694 -0.0306 0.0233 0.9999