XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-11X AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4318 0.08453 0.08224 -0.0388 0.9234 0.0178 -8.750 -0.4313 0.08024 0.07796 -0.0424 0.9223 0.0180 -8.500 -0.4356 0.07408 0.07178 -0.0500 0.9209 0.0181 -8.250 -0.4392 0.06957 0.06722 -0.0531 0.9195 0.0182 -8.000 -0.4376 0.06522 0.06279 -0.0557 0.9183 0.0185 -7.750 -0.4339 0.06107 0.05854 -0.0574 0.9167 0.0188 -7.500 -0.4279 0.05702 0.05437 -0.0585 0.9155 0.0193 -7.250 -0.4201 0.05287 0.05004 -0.0590 0.9144 0.0200 -7.000 -0.4143 0.04749 0.04398 -0.0573 0.9128 0.0213 -6.750 -0.4067 0.04276 0.03922 -0.0571 0.9120 0.0218 -6.500 -0.3902 0.04089 0.03732 -0.0569 0.9114 0.0222 -6.250 -0.3730 0.03904 0.03538 -0.0565 0.9107 0.0227 -6.000 -0.3559 0.03700 0.03318 -0.0556 0.9099 0.0236 -5.750 -0.3381 0.03471 0.03061 -0.0540 0.9089 0.0253 -5.500 -0.3266 0.03164 0.02698 -0.0508 0.9076 0.0269 -5.250 -0.3052 0.02976 0.02508 -0.0506 0.9063 0.0275 -5.000 -0.2821 0.02831 0.02356 -0.0504 0.9053 0.0283 -4.750 -0.2584 0.02699 0.02208 -0.0500 0.9043 0.0300 -4.500 -0.2370 0.02538 0.02001 -0.0484 0.9033 0.0334 -4.250 -0.2130 0.02391 0.01855 -0.0482 0.9019 0.0345 -4.000 -0.1906 0.02286 0.01740 -0.0470 0.8987 0.0364 -3.750 -0.1647 0.01805 0.01183 -0.0433 0.8962 0.0199 -3.500 -0.1430 0.01669 0.01031 -0.0411 0.8934 0.0193 -3.250 -0.1172 0.01579 0.00933 -0.0404 0.8907 0.0195 -3.000 -0.0915 0.01507 0.00856 -0.0398 0.8872 0.0198 -2.750 -0.0685 0.01440 0.00785 -0.0384 0.8834 0.0203 -2.500 -0.0464 0.01397 0.00735 -0.0365 0.8799 0.0212 -2.250 -0.0252 0.01321 0.00659 -0.0348 0.8753 0.0224 -2.000 -0.0023 0.01267 0.00604 -0.0334 0.8700 0.0233 -1.750 0.0201 0.01219 0.00552 -0.0316 0.8661 0.0247 -1.500 0.0439 0.01180 0.00510 -0.0303 0.8613 0.0266 -1.250 0.0684 0.01138 0.00467 -0.0292 0.8558 0.0309 -1.000 0.0920 0.01094 0.00426 -0.0278 0.8518 0.0457 -0.750 0.0984 0.00881 0.00392 -0.0240 0.8469 0.5576 -0.500 0.1743 0.00758 0.00400 -0.0335 0.8410 0.9412 -0.250 0.2347 0.00808 0.00441 -0.0392 0.8369 0.9814 0.000 0.2919 0.00820 0.00447 -0.0452 0.8306 0.9936 0.250 0.3394 0.00803 0.00423 -0.0491 0.8236 0.9993 0.500 0.3684 0.00786 0.00403 -0.0495 0.8154 1.0000 0.750 0.3928 0.00764 0.00376 -0.0486 0.8063 1.0000 1.000 0.4188 0.00744 0.00355 -0.0482 0.7919 1.0000 1.250 0.4449 0.00726 0.00333 -0.0478 0.7625 1.0000 1.500 0.4691 0.00764 0.00287 -0.0469 0.5957 1.0000 1.750 0.4968 0.00827 0.00304 -0.0474 0.5055 1.0000 2.000 0.5226 0.00892 0.00321 -0.0476 0.4102 1.0000 2.250 0.5473 0.00947 0.00337 -0.0475 0.3369 1.0000 2.500 0.5717 0.00988 0.00352 -0.0472 0.2902 1.0000 2.750 0.5959 0.01023 0.00365 -0.0468 0.2507 1.0000 3.000 0.6199 0.01054 0.00379 -0.0463 0.2276 1.0000 3.250 0.6440 0.01078 0.00394 -0.0457 0.2151 1.0000 3.500 0.6681 0.01101 0.00411 -0.0452 0.2069 1.0000 3.750 0.6920 0.01121 0.00427 -0.0446 0.2010 1.0000 4.000 0.7153 0.01150 0.00448 -0.0439 0.1956 1.0000 4.250 0.7390 0.01169 0.00467 -0.0432 0.1923 1.0000 4.500 0.7627 0.01188 0.00487 -0.0425 0.1890 1.0000 4.750 0.7859 0.01210 0.00507 -0.0417 0.1854 1.0000 5.000 0.8081 0.01242 0.00534 -0.0408 0.1808 1.0000 5.250 0.8308 0.01267 0.00558 -0.0400 0.1773 1.0000 5.500 0.8543 0.01282 0.00576 -0.0393 0.1737 1.0000 5.750 0.8772 0.01303 0.00598 -0.0385 0.1702 1.0000 6.000 0.8991 0.01332 0.00623 -0.0375 0.1664 1.0000 6.250 0.9201 0.01372 0.00661 -0.0364 0.1626 1.0000 6.500 0.9432 0.01387 0.00681 -0.0356 0.1606 1.0000 6.750 0.9658 0.01407 0.00705 -0.0348 0.1582 1.0000 7.000 0.9880 0.01429 0.00729 -0.0338 0.1554 1.0000 7.250 1.0097 0.01454 0.00754 -0.0329 0.1521 1.0000 7.500 1.0296 0.01497 0.00794 -0.0316 0.1481 1.0000 7.750 1.0517 0.01517 0.00819 -0.0307 0.1458 1.0000 8.000 1.0739 0.01532 0.00841 -0.0298 0.1430 1.0000 8.250 1.0956 0.01552 0.00865 -0.0288 0.1400 1.0000 8.500 1.1164 0.01576 0.00890 -0.0277 0.1368 1.0000 8.750 1.1351 0.01619 0.00931 -0.0263 0.1328 1.0000 9.000 1.1571 0.01631 0.00952 -0.0254 0.1302 1.0000 9.250 1.1783 0.01649 0.00976 -0.0244 0.1265 1.0000 9.500 1.1984 0.01672 0.01000 -0.0232 0.1221 1.0000 9.750 1.2173 0.01705 0.01034 -0.0218 0.1181 1.0000 10.000 1.2376 0.01727 0.01064 -0.0207 0.1138 1.0000 10.250 1.2549 0.01756 0.01093 -0.0190 0.1090 1.0000 10.500 1.2706 0.01789 0.01129 -0.0171 0.1044 1.0000 10.750 1.2869 0.01821 0.01166 -0.0153 0.0988 1.0000 11.000 1.3024 0.01862 0.01207 -0.0134 0.0926 1.0000 11.250 1.3178 0.01909 0.01253 -0.0117 0.0856 1.0000 11.500 1.3330 0.01961 0.01306 -0.0099 0.0793 1.0000 11.750 1.3467 0.02025 0.01370 -0.0081 0.0724 1.0000 12.000 1.3608 0.02090 0.01437 -0.0063 0.0657 1.0000 12.250 1.3736 0.02166 0.01514 -0.0044 0.0588 1.0000 12.500 1.3847 0.02257 0.01605 -0.0024 0.0512 1.0000 12.750 1.3947 0.02357 0.01704 -0.0003 0.0436 1.0000 13.000 1.4047 0.02458 0.01806 0.0017 0.0381 1.0000 13.250 1.4143 0.02560 0.01914 0.0037 0.0350 1.0000 13.500 1.4233 0.02669 0.02027 0.0056 0.0329 1.0000 13.750 1.4301 0.02793 0.02157 0.0077 0.0312 1.0000 14.000 1.4374 0.02915 0.02288 0.0096 0.0302 1.0000 14.250 1.4446 0.03039 0.02422 0.0115 0.0294 1.0000 14.500 1.4507 0.03174 0.02568 0.0133 0.0287 1.0000 14.750 1.4552 0.03324 0.02728 0.0150 0.0280 1.0000 15.000 1.4575 0.03496 0.02910 0.0168 0.0273 1.0000 15.250 1.4571 0.03697 0.03120 0.0185 0.0266 1.0000 15.500 1.4533 0.03937 0.03369 0.0201 0.0259 1.0000 15.750 1.4462 0.04221 0.03665 0.0215 0.0254 1.0000 16.000 1.4435 0.04484 0.03942 0.0223 0.0251 1.0000 16.250 1.4397 0.04779 0.04251 0.0227 0.0249 1.0000 16.500 1.4340 0.05127 0.04613 0.0225 0.0246 1.0000 16.750 1.4260 0.05535 0.05036 0.0218 0.0243 1.0000 17.000 1.4151 0.06015 0.05532 0.0203 0.0241 1.0000 17.250 1.4018 0.06565 0.06097 0.0183 0.0240 1.0000 17.500 1.3852 0.07194 0.06742 0.0156 0.0239 1.0000 17.750 1.3656 0.07891 0.07455 0.0124 0.0238 1.0000 18.000 1.3439 0.08636 0.08216 0.0091 0.0237 1.0000 18.250 1.3213 0.09399 0.08993 0.0056 0.0237 1.0000