XFOIL Version 6.96 Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.7544 0.07879 0.07241 -0.0506 1.0000 0.0443 -11.750 -0.8087 0.06853 0.06191 -0.0557 1.0000 0.0437 -11.500 -0.8435 0.06278 0.05595 -0.0565 1.0000 0.0436 -11.250 -0.8708 0.05866 0.05164 -0.0555 1.0000 0.0436 -11.000 -0.8947 0.05549 0.04831 -0.0532 1.0000 0.0437 -10.750 -0.9148 0.05269 0.04533 -0.0506 1.0000 0.0439 -10.500 -0.9247 0.04954 0.04193 -0.0496 1.0000 0.0444 -10.250 -0.9279 0.04644 0.03852 -0.0490 1.0000 0.0449 -10.000 -0.9253 0.04350 0.03524 -0.0484 1.0000 0.0455 -9.750 -0.9179 0.04076 0.03211 -0.0478 1.0000 0.0463 -9.500 -0.9053 0.03857 0.02966 -0.0472 1.0000 0.0471 -9.250 -0.8890 0.03711 0.02815 -0.0465 1.0000 0.0479 -9.000 -0.8718 0.03578 0.02675 -0.0460 1.0000 0.0491 -8.750 -0.8536 0.03441 0.02523 -0.0456 1.0000 0.0508 -8.500 -0.8344 0.03292 0.02349 -0.0451 1.0000 0.0528 -8.250 -0.8145 0.03153 0.02195 -0.0445 1.0000 0.0545 -8.000 -0.7940 0.03048 0.02092 -0.0440 1.0000 0.0560 -7.750 -0.7727 0.02945 0.01983 -0.0435 1.0000 0.0581 -7.500 -0.7506 0.02846 0.01867 -0.0430 1.0000 0.0609 -7.250 -0.7285 0.02749 0.01768 -0.0426 1.0000 0.0635 -7.000 -0.7057 0.02665 0.01687 -0.0423 1.0000 0.0662 -6.750 -0.6822 0.02586 0.01598 -0.0419 1.0000 0.0699 -6.500 -0.6585 0.02505 0.01518 -0.0417 1.0000 0.0736 -6.250 -0.6340 0.02433 0.01448 -0.0417 1.0000 0.0779 -6.000 -0.6090 0.02364 0.01373 -0.0415 1.0000 0.0831 -5.750 -0.5832 0.02294 0.01311 -0.0418 1.0000 0.0889 -5.500 -0.5570 0.02230 0.01247 -0.0420 1.0000 0.0960 -5.250 -0.5299 0.02169 0.01191 -0.0424 1.0000 0.1051 -5.000 -0.5022 0.02109 0.01141 -0.0430 1.0000 0.1160 -4.750 -0.4741 0.02056 0.01098 -0.0435 1.0000 0.1306 -4.500 -0.4457 0.02008 0.01061 -0.0441 1.0000 0.1499 -4.250 -0.4170 0.01962 0.01033 -0.0448 1.0000 0.1757 -4.000 -0.3872 0.01915 0.01007 -0.0457 1.0000 0.2126 -3.750 -0.3534 0.01851 0.00979 -0.0479 1.0000 0.2721 -3.500 -0.3128 0.01755 0.00965 -0.0519 1.0000 0.4010 -3.250 -0.3120 0.01839 0.01124 -0.0440 1.0000 0.4982 -3.000 -0.3163 0.01982 0.01296 -0.0344 1.0000 0.5477 -2.500 -0.2442 0.02040 0.01328 -0.0388 1.0000 0.6387 -2.000 -0.1914 0.02129 0.01402 -0.0380 1.0000 0.6712 -1.750 -0.1713 0.02176 0.01448 -0.0359 1.0000 0.6831 -1.250 -0.1285 0.02243 0.01512 -0.0326 1.0000 0.7034 -1.000 -0.1138 0.02273 0.01545 -0.0292 1.0000 0.7107 -0.750 -0.0940 0.02302 0.01576 -0.0272 1.0000 0.7215 -0.500 -0.0713 0.02334 0.01609 -0.0260 1.0000 0.7344 -0.250 -0.0610 0.02349 0.01631 -0.0217 1.0000 0.7412 0.000 -0.0312 0.02363 0.01645 -0.0226 0.9996 0.7494 0.250 0.0189 0.02383 0.01667 -0.0270 0.9887 0.7526 0.500 0.0672 0.02387 0.01674 -0.0308 0.9764 0.7550 0.750 0.1145 0.02373 0.01664 -0.0344 0.9633 0.7574 1.000 0.1635 0.02339 0.01635 -0.0382 0.9482 0.7596 1.250 0.2095 0.02290 0.01594 -0.0414 0.9321 0.7618 1.500 0.2466 0.02232 0.01544 -0.0429 0.9102 0.7640 1.750 0.2857 0.02169 0.01491 -0.0447 0.8850 0.7658 2.000 0.3106 0.02121 0.01452 -0.0436 0.8481 0.7675 2.250 0.4264 0.02038 0.01218 -0.0564 0.4853 0.7672 2.500 0.4510 0.02129 0.01233 -0.0559 0.3401 0.7684 2.750 0.4770 0.02192 0.01250 -0.0559 0.2510 0.7694 3.000 0.5026 0.02246 0.01271 -0.0558 0.1936 0.7708 3.250 0.5285 0.02294 0.01299 -0.0556 0.1565 0.7724 3.500 0.5552 0.02343 0.01332 -0.0557 0.1311 0.7737 3.750 0.5824 0.02395 0.01370 -0.0559 0.1142 0.7747 4.000 0.6099 0.02445 0.01416 -0.0562 0.1017 0.7758 4.250 0.6375 0.02498 0.01469 -0.0563 0.0924 0.7772 4.500 0.6651 0.02561 0.01527 -0.0567 0.0852 0.7786 4.750 0.6937 0.02621 0.01589 -0.0571 0.0792 0.7797 5.000 0.7220 0.02694 0.01657 -0.0576 0.0745 0.7805 5.250 0.7514 0.02762 0.01732 -0.0582 0.0697 0.7813 5.500 0.7804 0.02845 0.01808 -0.0589 0.0665 0.7822 5.750 0.8077 0.02930 0.01904 -0.0589 0.0632 0.7832 6.000 0.8335 0.03006 0.01990 -0.0586 0.0601 0.7841 6.250 0.8596 0.03093 0.02074 -0.0586 0.0578 0.7849 6.500 0.8869 0.03211 0.02203 -0.0587 0.0559 0.7854 6.750 0.9137 0.03328 0.02344 -0.0587 0.0536 0.7860 7.000 0.9393 0.03432 0.02460 -0.0586 0.0515 0.7866 7.250 0.9645 0.03538 0.02568 -0.0586 0.0500 0.7872 7.500 0.9889 0.03698 0.02748 -0.0583 0.0488 0.7880 7.750 1.0111 0.03894 0.02983 -0.0576 0.0476 0.7890 8.000 1.0314 0.04100 0.03227 -0.0568 0.0465 0.7900 8.250 1.0505 0.04299 0.03456 -0.0559 0.0454 0.7909 8.500 1.0694 0.04472 0.03651 -0.0551 0.0443 0.7915 8.750 1.0882 0.04632 0.03824 -0.0545 0.0434 0.7921 9.000 1.1051 0.04823 0.04028 -0.0538 0.0426 0.7927 9.250 1.1074 0.05195 0.04466 -0.0512 0.0419 0.7932 9.500 1.1056 0.05592 0.04916 -0.0486 0.0415 0.7937 9.750 1.0976 0.06019 0.05391 -0.0458 0.0412 0.7941 10.000 1.0817 0.06468 0.05882 -0.0427 0.0411 0.7946 10.250 1.0579 0.06929 0.06378 -0.0397 0.0410 0.7951 10.500 1.0294 0.07492 0.06972 -0.0384 0.0411 0.7957 10.750 0.9944 0.08219 0.07729 -0.0399 0.0413 0.7961 11.000 0.9491 0.09414 0.08950 -0.0483 0.0418 0.7964