XFOIL Version 6.96 Calculated polar for: LOCKHEED C-141 BL0 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 ------ -------- --------- --------- -------- -------- -------- -13.000 -0.4341 0.12258 0.11884 -0.0452 1.0000 0.0788 -12.750 -0.4439 0.11720 0.11349 -0.0461 1.0000 0.0794 -12.500 -0.8075 0.06345 0.05874 -0.0729 1.0000 0.0437 -12.250 -0.8327 0.06009 0.05528 -0.0703 1.0000 0.0436 -12.000 -0.8591 0.05745 0.05253 -0.0661 1.0000 0.0434 -11.750 -0.8874 0.05546 0.05043 -0.0603 1.0000 0.0434 -11.500 -0.9161 0.05386 0.04874 -0.0533 1.0000 0.0433 -11.250 -0.9405 0.05158 0.04628 -0.0471 1.0000 0.0433 -11.000 -0.9610 0.04906 0.04353 -0.0413 1.0000 0.0433 -10.750 -0.9777 0.04644 0.04062 -0.0358 1.0000 0.0434 -10.500 -0.9898 0.04386 0.03769 -0.0306 1.0000 0.0435 -10.250 -0.9972 0.04133 0.03479 -0.0259 1.0000 0.0439 -10.000 -0.9936 0.03856 0.03187 -0.0232 1.0000 0.0445 -9.750 -0.9844 0.03703 0.03027 -0.0208 1.0000 0.0453 -9.500 -0.9723 0.03601 0.02921 -0.0187 1.0000 0.0465 -9.250 -0.9623 0.03469 0.02772 -0.0161 1.0000 0.0479 -9.000 -0.9529 0.03308 0.02579 -0.0134 1.0000 0.0494 -8.750 -0.9425 0.03168 0.02397 -0.0106 1.0000 0.0507 -8.500 -0.9261 0.02966 0.02188 -0.0092 1.0000 0.0522 -8.250 -0.9090 0.02871 0.02088 -0.0077 1.0000 0.0539 -8.000 -0.8917 0.02785 0.01992 -0.0061 1.0000 0.0560 -7.750 -0.8744 0.02706 0.01887 -0.0044 1.0000 0.0585 -7.500 -0.8552 0.02569 0.01746 -0.0032 1.0000 0.0609 -7.250 -0.8361 0.02500 0.01676 -0.0020 1.0000 0.0634 -7.000 -0.8168 0.02437 0.01601 -0.0006 1.0000 0.0665 -6.750 -0.7969 0.02344 0.01497 0.0006 1.0000 0.0696 -6.500 -0.7771 0.02275 0.01434 0.0017 1.0000 0.0728 -6.250 -0.7570 0.02227 0.01378 0.0029 1.0000 0.0767 -6.000 -0.7366 0.02151 0.01296 0.0041 1.0000 0.0806 -5.750 -0.7166 0.02094 0.01246 0.0052 1.0000 0.0848 -5.500 -0.6874 0.02064 0.01205 0.0046 0.9983 0.0904 -5.250 -0.6549 0.01994 0.01147 0.0031 0.9957 0.0973 -5.000 -0.6212 0.01956 0.01105 0.0016 0.9930 0.1057 -4.750 -0.5904 0.01915 0.01069 0.0005 0.9895 0.1155 -4.500 -0.5579 0.01871 0.01034 -0.0009 0.9863 0.1287 -4.250 -0.5226 0.01841 0.01009 -0.0029 0.9837 0.1478 -4.000 -0.4956 0.01783 0.00973 -0.0033 0.9794 0.1737 -3.750 -0.4653 0.01725 0.00946 -0.0044 0.9756 0.2227 -3.500 -0.4343 0.01637 0.00924 -0.0060 0.9728 0.3454 -3.250 -0.4079 0.01546 0.00927 -0.0063 0.9695 0.5340 -3.000 -0.3839 0.01517 0.00941 -0.0055 0.9642 0.6372 -2.750 -0.3516 0.01524 0.00964 -0.0061 0.9604 0.7001 -2.500 -0.3148 0.01544 0.00992 -0.0077 0.9576 0.7422 -2.250 -0.2937 0.01543 0.00995 -0.0062 0.9507 0.7717 -2.000 -0.2619 0.01555 0.01014 -0.0066 0.9464 0.7985 -1.750 -0.2256 0.01575 0.01036 -0.0080 0.9433 0.8239 -1.500 -0.2045 0.01583 0.01049 -0.0063 0.9363 0.8444 -1.250 -0.1737 0.01599 0.01066 -0.0064 0.9314 0.8644 -1.000 -0.1374 0.01620 0.01088 -0.0076 0.9283 0.8832 -0.750 -0.1142 0.01639 0.01108 -0.0062 0.9214 0.9014 -0.500 -0.0815 0.01667 0.01137 -0.0065 0.9165 0.9215 -0.250 -0.0383 0.01709 0.01177 -0.0088 0.9139 0.9405 0.000 0.0171 0.01740 0.01206 -0.0141 0.9126 0.9467 0.250 0.0673 0.01754 0.01218 -0.0188 0.9105 0.9522 0.500 0.1039 0.01765 0.01230 -0.0209 0.9028 0.9592 0.750 0.1577 0.01767 0.01232 -0.0263 0.9000 0.9619 1.000 0.2124 0.01759 0.01226 -0.0318 0.8979 0.9648 1.250 0.2721 0.01728 0.01197 -0.0381 0.8959 0.9661 1.500 0.3195 0.01662 0.01133 -0.0413 0.8849 0.9701 1.750 0.3906 0.01541 0.01015 -0.0486 0.8803 0.9669 2.000 0.4302 0.01495 0.00974 -0.0506 0.8697 0.9719 2.250 0.4837 0.01416 0.00900 -0.0550 0.8638 0.9733 2.500 0.5244 0.01368 0.00858 -0.0572 0.8507 0.9778 2.750 0.5624 0.01319 0.00815 -0.0587 0.8361 0.9834 3.000 0.6055 0.01264 0.00764 -0.0613 0.8170 0.9869 3.250 0.6441 0.01222 0.00726 -0.0631 0.7889 0.9921 3.500 0.6846 0.01179 0.00676 -0.0652 0.7451 0.9959 3.750 0.7233 0.01166 0.00628 -0.0668 0.6705 0.9994 4.000 0.7383 0.01204 0.00621 -0.0641 0.5793 1.0000 4.250 0.7407 0.01277 0.00635 -0.0593 0.4681 1.0000 4.500 0.7380 0.01370 0.00666 -0.0539 0.3566 1.0000 4.750 0.7375 0.01457 0.00703 -0.0489 0.2733 1.0000 5.000 0.7405 0.01529 0.00741 -0.0445 0.2199 1.0000 5.250 0.7460 0.01591 0.00780 -0.0406 0.1861 1.0000 5.500 0.7539 0.01644 0.00819 -0.0369 0.1623 1.0000 5.750 0.7623 0.01697 0.00860 -0.0334 0.1451 1.0000 6.000 0.7716 0.01749 0.00905 -0.0299 0.1318 1.0000 6.250 0.7811 0.01808 0.00954 -0.0265 0.1212 1.0000 6.500 0.7922 0.01861 0.01001 -0.0235 0.1122 1.0000 6.750 0.8048 0.01917 0.01057 -0.0207 0.1044 1.0000 7.000 0.8170 0.01986 0.01116 -0.0179 0.0976 1.0000 7.250 0.8319 0.02041 0.01176 -0.0155 0.0918 1.0000 7.500 0.8459 0.02101 0.01232 -0.0131 0.0866 1.0000 7.750 0.8636 0.02184 0.01315 -0.0114 0.0816 1.0000 8.000 0.8802 0.02243 0.01376 -0.0094 0.0772 1.0000 8.250 0.9033 0.02359 0.01483 -0.0090 0.0728 1.0000 8.500 0.9207 0.02419 0.01555 -0.0072 0.0692 1.0000 8.750 0.9396 0.02492 0.01628 -0.0058 0.0659 1.0000 9.000 0.9663 0.02631 0.01764 -0.0061 0.0625 1.0000 9.250 0.9840 0.02707 0.01856 -0.0044 0.0597 1.0000 9.500 1.0034 0.02797 0.01951 -0.0032 0.0573 1.0000 9.750 1.0331 0.02976 0.02120 -0.0042 0.0547 1.0000 10.000 1.0482 0.03083 0.02254 -0.0022 0.0530 1.0000 10.250 1.0642 0.03195 0.02384 -0.0004 0.0510 1.0000 10.500 1.0801 0.03300 0.02497 0.0012 0.0492 1.0000 10.750 1.1001 0.03438 0.02635 0.0019 0.0478 1.0000 11.000 1.1183 0.03690 0.02905 0.0027 0.0466 1.0000 11.250 1.1233 0.03865 0.03116 0.0060 0.0458 1.0000 11.500 1.1253 0.04064 0.03347 0.0095 0.0450 1.0000 11.750 1.1250 0.04270 0.03581 0.0131 0.0442 1.0000 12.000 1.1236 0.04472 0.03808 0.0166 0.0435 1.0000 12.250 1.1228 0.04664 0.04018 0.0197 0.0427 1.0000 12.500 1.1253 0.04837 0.04201 0.0221 0.0420 1.0000 12.750 1.1307 0.05010 0.04381 0.0240 0.0414 1.0000 13.000 1.1270 0.05261 0.04647 0.0265 0.0410 1.0000 13.250 1.1181 0.05563 0.04968 0.0291 0.0407 1.0000 13.500 1.1025 0.05909 0.05337 0.0317 0.0406 1.0000 13.750 1.0809 0.06295 0.05749 0.0340 0.0407 1.0000 14.000 1.0462 0.06801 0.06289 0.0355 0.0409 1.0000