XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-5 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.8958 0.02704 0.02338 -0.0408 0.7985 0.0071 -10.750 -0.8777 0.02472 0.02076 -0.0407 0.7901 0.0072 -10.500 -0.8568 0.02307 0.01886 -0.0405 0.7804 0.0073 -10.250 -0.8341 0.02176 0.01735 -0.0404 0.7699 0.0073 -10.000 -0.8125 0.02010 0.01543 -0.0403 0.7596 0.0075 -9.750 -0.7890 0.01889 0.01402 -0.0402 0.7493 0.0077 -9.500 -0.7640 0.01805 0.01303 -0.0402 0.7397 0.0079 -9.250 -0.7383 0.01736 0.01222 -0.0401 0.7312 0.0081 -9.000 -0.7122 0.01672 0.01146 -0.0401 0.7228 0.0084 -8.750 -0.6860 0.01608 0.01070 -0.0401 0.7154 0.0086 -8.500 -0.6596 0.01545 0.00993 -0.0401 0.7078 0.0087 -8.250 -0.6330 0.01485 0.00921 -0.0402 0.7013 0.0089 -8.000 -0.6061 0.01429 0.00853 -0.0402 0.6950 0.0091 -7.750 -0.5791 0.01378 0.00791 -0.0402 0.6892 0.0093 -7.500 -0.5518 0.01329 0.00733 -0.0402 0.6841 0.0095 -7.250 -0.5244 0.01286 0.00681 -0.0403 0.6785 0.0097 -7.000 -0.4970 0.01237 0.00622 -0.0404 0.6732 0.0100 -6.750 -0.4694 0.01197 0.00578 -0.0404 0.6683 0.0105 -6.500 -0.4414 0.01166 0.00542 -0.0406 0.6628 0.0110 -6.000 -0.3853 0.01106 0.00471 -0.0408 0.6517 0.0118 -5.750 -0.3571 0.01078 0.00436 -0.0409 0.6456 0.0123 -5.500 -0.3289 0.01051 0.00405 -0.0411 0.6402 0.0129 -5.250 -0.3004 0.01029 0.00382 -0.0413 0.6347 0.0138 -5.000 -0.2719 0.01011 0.00359 -0.0414 0.6288 0.0150 -4.750 -0.2433 0.00992 0.00337 -0.0416 0.6236 0.0161 -4.500 -0.2146 0.00979 0.00323 -0.0418 0.6178 0.0176 -4.250 -0.1858 0.00967 0.00308 -0.0420 0.6119 0.0190 -4.000 -0.1571 0.00954 0.00291 -0.0423 0.6063 0.0201 -3.750 -0.1283 0.00940 0.00277 -0.0425 0.6000 0.0214 -3.500 -0.0995 0.00930 0.00264 -0.0427 0.5945 0.0226 -3.250 -0.0706 0.00918 0.00249 -0.0430 0.5893 0.0236 -3.000 -0.0417 0.00907 0.00234 -0.0432 0.5842 0.0243 -2.750 -0.0128 0.00895 0.00219 -0.0435 0.5796 0.0252 -2.500 0.0161 0.00879 0.00201 -0.0437 0.5750 0.0267 -2.250 0.0450 0.00869 0.00189 -0.0440 0.5703 0.0279 -2.000 0.0740 0.00862 0.00179 -0.0443 0.5654 0.0293 -1.750 0.1031 0.00853 0.00169 -0.0446 0.5606 0.0304 -1.500 0.1321 0.00846 0.00159 -0.0448 0.5557 0.0311 -1.250 0.1611 0.00837 0.00147 -0.0451 0.5521 0.0330 -1.000 0.1902 0.00829 0.00140 -0.0454 0.5492 0.0358 -0.750 0.2193 0.00822 0.00134 -0.0457 0.5457 0.0388 -0.500 0.2484 0.00817 0.00128 -0.0460 0.5410 0.0450 -0.250 0.2773 0.00807 0.00124 -0.0463 0.5364 0.0696 0.000 0.3062 0.00790 0.00122 -0.0467 0.5333 0.1269 0.250 0.3344 0.00724 0.00115 -0.0473 0.5302 0.3496 0.500 0.3620 0.00652 0.00112 -0.0478 0.5270 0.5795 1.000 0.4194 0.00637 0.00118 -0.0483 0.5201 0.6693 1.250 0.4481 0.00628 0.00122 -0.0486 0.5168 0.7089 1.500 0.4764 0.00620 0.00129 -0.0487 0.5127 0.7564 1.750 0.5051 0.00620 0.00133 -0.0489 0.5090 0.7769 2.000 0.5340 0.00624 0.00138 -0.0492 0.5057 0.7872 2.250 0.5630 0.00626 0.00143 -0.0494 0.5026 0.7965 2.500 0.5920 0.00629 0.00147 -0.0497 0.4978 0.8058 2.750 0.6207 0.00632 0.00153 -0.0500 0.4918 0.8154 3.000 0.6494 0.00636 0.00159 -0.0502 0.4868 0.8257 3.250 0.6780 0.00639 0.00166 -0.0504 0.4807 0.8383 3.750 0.7341 0.00648 0.00182 -0.0507 0.4638 0.8692 4.000 0.7616 0.00657 0.00192 -0.0507 0.4495 0.8860 4.250 0.7884 0.00672 0.00204 -0.0506 0.4282 0.9039 4.500 0.8144 0.00700 0.00221 -0.0505 0.3955 0.9212 4.750 0.8400 0.00731 0.00242 -0.0503 0.3651 0.9376 5.000 0.8650 0.00779 0.00271 -0.0502 0.3160 0.9558 5.250 0.8944 0.00843 0.00310 -0.0512 0.2635 0.9847 5.500 0.9219 0.00888 0.00342 -0.0517 0.2350 1.0000 5.750 0.9488 0.00924 0.00368 -0.0519 0.2145 1.0000 6.000 0.9738 0.00986 0.00408 -0.0521 0.1695 1.0000 6.250 0.9974 0.01064 0.00461 -0.0521 0.1240 1.0000 6.500 1.0232 0.01108 0.00497 -0.0522 0.1060 1.0000 6.750 1.0474 0.01169 0.00543 -0.0522 0.0780 1.0000 7.000 1.0721 0.01220 0.00585 -0.0522 0.0623 1.0000 7.250 1.0971 0.01264 0.00624 -0.0522 0.0521 1.0000 7.500 1.1218 0.01309 0.00665 -0.0522 0.0425 1.0000 7.750 1.1462 0.01355 0.00707 -0.0521 0.0352 1.0000 8.000 1.1705 0.01398 0.00749 -0.0520 0.0299 1.0000 8.250 1.1943 0.01446 0.00794 -0.0519 0.0255 1.0000 8.500 1.2177 0.01493 0.00841 -0.0517 0.0217 1.0000 8.750 1.2406 0.01543 0.00891 -0.0515 0.0183 1.0000 9.000 1.2626 0.01597 0.00945 -0.0512 0.0156 1.0000 9.250 1.2844 0.01650 0.01000 -0.0508 0.0141 1.0000 9.500 1.3052 0.01708 0.01059 -0.0504 0.0130 1.0000 9.750 1.3251 0.01769 0.01123 -0.0499 0.0123 1.0000 10.000 1.3440 0.01831 0.01189 -0.0492 0.0118 1.0000 10.250 1.3603 0.01903 0.01265 -0.0484 0.0114 1.0000 10.500 1.3757 0.01983 0.01350 -0.0475 0.0111 1.0000 10.750 1.3903 0.02073 0.01445 -0.0467 0.0109 1.0000 11.000 1.4041 0.02173 0.01549 -0.0459 0.0106 1.0000 11.250 1.4169 0.02283 0.01665 -0.0451 0.0103 1.0000 11.500 1.4284 0.02406 0.01793 -0.0443 0.0100 1.0000 11.750 1.4381 0.02547 0.01940 -0.0434 0.0096 1.0000 12.000 1.4490 0.02682 0.02081 -0.0427 0.0094 1.0000 12.250 1.4597 0.02821 0.02227 -0.0421 0.0093 1.0000 12.500 1.4695 0.02970 0.02383 -0.0415 0.0092 1.0000 12.750 1.4785 0.03130 0.02550 -0.0410 0.0091 1.0000 13.000 1.4868 0.03298 0.02726 -0.0404 0.0089 1.0000 13.250 1.4941 0.03478 0.02913 -0.0399 0.0088 1.0000 13.500 1.5010 0.03664 0.03105 -0.0395 0.0086 1.0000 13.750 1.5069 0.03861 0.03309 -0.0390 0.0084 1.0000 14.000 1.5118 0.04070 0.03526 -0.0386 0.0083 1.0000 14.250 1.5157 0.04290 0.03754 -0.0382 0.0081 1.0000 14.500 1.5185 0.04524 0.03995 -0.0378 0.0080 1.0000 14.750 1.5208 0.04773 0.04251 -0.0376 0.0079 1.0000 15.000 1.5222 0.05038 0.04525 -0.0375 0.0077 1.0000 15.250 1.5222 0.05324 0.04819 -0.0374 0.0076 1.0000 15.500 1.5206 0.05637 0.05140 -0.0375 0.0074 1.0000 15.750 1.5165 0.05988 0.05501 -0.0377 0.0073 1.0000 16.000 1.5113 0.06357 0.05879 -0.0380 0.0071 1.0000 16.250 1.5129 0.06647 0.06178 -0.0383 0.0071 1.0000 16.500 1.5135 0.06956 0.06496 -0.0387 0.0070 1.0000 16.750 1.5134 0.07279 0.06828 -0.0392 0.0069 1.0000 17.000 1.5121 0.07619 0.07177 -0.0398 0.0068 1.0000 17.250 1.5098 0.07980 0.07547 -0.0404 0.0067 1.0000 17.500 1.5063 0.08363 0.07940 -0.0413 0.0066 1.0000 17.750 1.5020 0.08766 0.08352 -0.0422 0.0065 1.0000 18.000 1.4966 0.09186 0.08783 -0.0433 0.0065 1.0000 18.250 1.4905 0.09626 0.09233 -0.0445 0.0064 1.0000 18.500 1.4840 0.10080 0.09698 -0.0459 0.0063 1.0000 18.750 1.4772 0.10547 0.10174 -0.0474 0.0062 1.0000 19.000 1.4690 0.11042 0.10680 -0.0492 0.0061 1.0000 19.250 1.4607 0.11541 0.11189 -0.0510 0.0060 1.0000