XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-7 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 -0.4092 0.09432 0.09088 -0.0396 1.0000 0.0471 -9.500 -0.4173 0.08895 0.08556 -0.0450 1.0000 0.0472 -9.250 -0.4338 0.08409 0.08069 -0.0498 1.0000 0.0472 -9.000 -0.4040 0.08224 0.07892 -0.0406 1.0000 0.0489 -8.750 -0.4006 0.07937 0.07609 -0.0407 1.0000 0.0497 -8.500 -0.4023 0.07601 0.07278 -0.0418 1.0000 0.0508 -8.250 -0.4163 0.07164 0.06848 -0.0449 1.0000 0.0512 -8.000 -0.4278 0.06806 0.06492 -0.0455 1.0000 0.0519 -7.750 -0.4376 0.06473 0.06161 -0.0453 1.0000 0.0527 -7.500 -0.4487 0.06187 0.05876 -0.0445 0.9979 0.0539 -7.250 -0.4320 0.05358 0.04964 -0.0555 0.9740 0.0590 -7.000 -0.3995 0.04958 0.04589 -0.0585 0.9637 0.0614 -6.750 -0.3684 0.04632 0.04246 -0.0623 0.9481 0.0665 -6.500 -0.3455 0.04163 0.03726 -0.0655 0.9289 0.0733 -6.250 -0.3178 0.03900 0.03455 -0.0671 0.9114 0.0770 -6.000 -0.3016 0.03639 0.03142 -0.0667 0.8909 0.0864 -5.750 -0.2802 0.03429 0.02929 -0.0663 0.8745 0.0906 -5.500 -0.2636 0.03241 0.02708 -0.0652 0.8592 0.1018 -5.250 -0.2455 0.03096 0.02538 -0.0641 0.8460 0.1153 -5.000 -0.2169 0.02492 0.01812 -0.0605 0.8351 0.0615 -4.750 -0.1905 0.02213 0.01459 -0.0584 0.8247 0.0488 -4.500 -0.1637 0.02166 0.01381 -0.0574 0.8155 0.0474 -4.250 -0.1380 0.02012 0.01209 -0.0567 0.8053 0.0471 -4.000 -0.1120 0.01901 0.01078 -0.0559 0.7959 0.0473 -3.750 -0.0869 0.01734 0.00907 -0.0553 0.7865 0.0495 -3.500 -0.0618 0.01657 0.00827 -0.0546 0.7767 0.0517 -3.250 -0.0366 0.01587 0.00750 -0.0538 0.7688 0.0534 -3.000 -0.0120 0.01528 0.00687 -0.0529 0.7599 0.0559 -2.500 0.0356 0.01417 0.00573 -0.0512 0.7450 0.0669 -2.250 0.0596 0.01366 0.00513 -0.0502 0.7383 0.0783 -2.000 0.0716 0.01172 0.00463 -0.0480 0.7306 0.4051 -1.750 0.0835 0.01083 0.00476 -0.0442 0.7241 0.6910 -1.500 0.1052 0.01062 0.00486 -0.0420 0.7172 0.7872 -1.250 0.1347 0.01060 0.00498 -0.0411 0.7102 0.8680 -1.000 0.1775 0.01082 0.00516 -0.0429 0.7034 0.9255 -0.750 0.2320 0.01107 0.00527 -0.0475 0.6956 0.9514 -0.500 0.2857 0.01123 0.00525 -0.0524 0.6886 0.9662 -0.250 0.3340 0.01127 0.00517 -0.0567 0.6803 0.9777 0.000 0.3808 0.01128 0.00504 -0.0608 0.6733 0.9882 0.250 0.4291 0.01124 0.00491 -0.0654 0.6647 0.9984 0.500 0.4541 0.01124 0.00478 -0.0653 0.6583 1.0000 0.750 0.4737 0.01125 0.00477 -0.0641 0.6502 1.0000 1.000 0.4954 0.01131 0.00471 -0.0630 0.6440 1.0000 1.250 0.5161 0.01138 0.00479 -0.0619 0.6357 1.0000 1.500 0.5388 0.01147 0.00477 -0.0609 0.6293 1.0000 1.750 0.5607 0.01157 0.00487 -0.0599 0.6212 1.0000 2.000 0.5839 0.01166 0.00490 -0.0590 0.6144 1.0000 2.250 0.6065 0.01178 0.00502 -0.0581 0.6065 1.0000 2.500 0.6301 0.01188 0.00505 -0.0572 0.5993 1.0000 2.750 0.6531 0.01200 0.00519 -0.0563 0.5913 1.0000 3.000 0.6770 0.01209 0.00522 -0.0555 0.5837 1.0000 3.250 0.7001 0.01220 0.00535 -0.0546 0.5749 1.0000 3.500 0.7245 0.01228 0.00535 -0.0538 0.5673 1.0000 3.750 0.7475 0.01240 0.00553 -0.0529 0.5579 1.0000 4.000 0.7724 0.01252 0.00558 -0.0522 0.5511 1.0000 4.250 0.7953 0.01266 0.00578 -0.0513 0.5416 1.0000 4.500 0.8193 0.01277 0.00588 -0.0505 0.5327 1.0000 4.750 0.8431 0.01288 0.00598 -0.0497 0.5232 1.0000 5.000 0.8664 0.01304 0.00618 -0.0488 0.5136 1.0000 5.250 0.8906 0.01318 0.00628 -0.0480 0.5048 1.0000 5.500 0.9136 0.01331 0.00647 -0.0471 0.4940 1.0000 5.750 0.9368 0.01348 0.00668 -0.0462 0.4838 1.0000 6.000 0.9601 0.01364 0.00683 -0.0453 0.4732 1.0000 6.250 0.9831 0.01379 0.00697 -0.0444 0.4611 1.0000 6.500 1.0049 0.01393 0.00717 -0.0433 0.4473 1.0000 6.750 1.0269 0.01411 0.00740 -0.0422 0.4340 1.0000 7.000 1.0492 0.01432 0.00768 -0.0412 0.4216 1.0000 7.250 1.0710 0.01455 0.00797 -0.0402 0.4083 1.0000 7.500 1.0921 0.01481 0.00825 -0.0390 0.3932 1.0000 7.750 1.1121 0.01510 0.00854 -0.0377 0.3755 1.0000 8.000 1.1308 0.01545 0.00889 -0.0362 0.3553 1.0000 8.250 1.1484 0.01581 0.00927 -0.0346 0.3299 1.0000 8.500 1.1640 0.01629 0.00970 -0.0327 0.3005 1.0000 8.750 1.1768 0.01696 0.01026 -0.0306 0.2678 1.0000 9.000 1.1871 0.01779 0.01096 -0.0281 0.2314 1.0000 9.500 1.1955 0.02008 0.01289 -0.0218 0.1691 1.0000 9.750 1.1965 0.02121 0.01392 -0.0181 0.1434 1.0000 10.000 1.1951 0.02252 0.01512 -0.0145 0.1244 1.0000 10.250 1.1948 0.02392 0.01647 -0.0114 0.1087 1.0000 10.500 1.1945 0.02549 0.01800 -0.0088 0.0966 1.0000 10.750 1.1919 0.02738 0.01983 -0.0065 0.0874 1.0000 11.000 1.1911 0.02934 0.02181 -0.0047 0.0792 1.0000 11.250 1.1903 0.03146 0.02398 -0.0032 0.0721 1.0000 11.500 1.1879 0.03381 0.02631 -0.0019 0.0667 1.0000 11.750 1.1895 0.03595 0.02853 -0.0007 0.0617 1.0000 12.000 1.1915 0.03810 0.03071 0.0001 0.0576 1.0000 12.250 1.1913 0.04050 0.03304 0.0015 0.0544 1.0000 12.500 1.1975 0.04239 0.03509 0.0022 0.0516 1.0000 12.750 1.2026 0.04440 0.03718 0.0028 0.0488 1.0000 13.000 1.2071 0.04646 0.03923 0.0035 0.0464 1.0000 13.250 1.2149 0.04837 0.04117 0.0046 0.0442 1.0000 13.500 1.2218 0.05036 0.04332 0.0052 0.0425 1.0000 13.750 1.2280 0.05241 0.04549 0.0056 0.0409 1.0000 14.000 1.2333 0.05455 0.04769 0.0059 0.0393 1.0000 14.250 1.2405 0.05657 0.04970 0.0064 0.0376 1.0000 14.500 1.2494 0.05886 0.05210 0.0073 0.0363 1.0000 14.750 1.2519 0.06153 0.05499 0.0074 0.0355 1.0000 15.000 1.2522 0.06451 0.05818 0.0074 0.0345 1.0000 15.250 1.2528 0.06758 0.06143 0.0073 0.0338 1.0000 15.500 1.2508 0.07083 0.06483 0.0067 0.0328 1.0000 15.750 1.2487 0.07430 0.06846 0.0062 0.0322 1.0000 16.000 1.2478 0.07749 0.07173 0.0054 0.0313 1.0000 16.250 1.2477 0.08083 0.07515 0.0048 0.0307 1.0000 16.500 1.2441 0.08517 0.07962 0.0043 0.0299 1.0000 16.750 1.2292 0.09079 0.08547 0.0023 0.0296 1.0000 17.000 1.2139 0.09661 0.09151 -0.0002 0.0295 1.0000 17.250 1.1952 0.10320 0.09834 -0.0035 0.0294 1.0000 17.500 1.1782 0.10989 0.10525 -0.0069 0.0294 1.0000 17.750 1.1572 0.11764 0.11320 -0.0112 0.0295 1.0000 18.000 1.1351 0.12597 0.12173 -0.0161 0.0295 1.0000 18.250 1.1126 0.13481 0.13075 -0.0213 0.0297 1.0000 18.500 1.0875 0.14496 0.14110 -0.0282 0.0300 1.0000