XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH TAB 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.6052 0.08038 0.07806 0.0075 0.8026 0.0098 -8.500 -0.6225 0.06967 0.06726 -0.0052 0.7905 0.0097 -8.250 -0.7012 0.03474 0.03086 -0.0175 0.7889 0.0107 -8.000 -0.6824 0.03267 0.02855 -0.0176 0.7771 0.0109 -7.750 -0.6606 0.03121 0.02688 -0.0177 0.7657 0.0111 -7.500 -0.6390 0.02920 0.02458 -0.0177 0.7544 0.0114 -7.250 -0.6166 0.02692 0.02199 -0.0177 0.7430 0.0117 -7.000 -0.5935 0.02441 0.01908 -0.0177 0.7321 0.0121 -6.750 -0.5692 0.02203 0.01627 -0.0176 0.7219 0.0126 -6.500 -0.5434 0.02013 0.01398 -0.0175 0.7122 0.0131 -6.250 -0.5161 0.01897 0.01250 -0.0175 0.7039 0.0136 -6.000 -0.4891 0.01780 0.01114 -0.0176 0.6964 0.0140 -5.750 -0.4614 0.01707 0.01030 -0.0178 0.6900 0.0144 -5.500 -0.4333 0.01640 0.00953 -0.0179 0.6836 0.0147 -5.250 -0.4051 0.01576 0.00877 -0.0181 0.6774 0.0150 -5.000 -0.3767 0.01514 0.00804 -0.0182 0.6708 0.0154 -4.750 -0.3481 0.01455 0.00734 -0.0184 0.6636 0.0158 -4.500 -0.3195 0.01401 0.00669 -0.0186 0.6574 0.0163 -4.250 -0.2905 0.01359 0.00619 -0.0188 0.6519 0.0169 -4.000 -0.2615 0.01319 0.00571 -0.0191 0.6465 0.0173 -3.750 -0.2327 0.01260 0.00507 -0.0194 0.6411 0.0179 -3.500 -0.2035 0.01221 0.00466 -0.0197 0.6350 0.0185 -3.250 -0.1741 0.01190 0.00430 -0.0200 0.6296 0.0192 -3.000 -0.1446 0.01161 0.00396 -0.0204 0.6251 0.0199 -2.750 -0.1149 0.01134 0.00365 -0.0207 0.6202 0.0207 -2.500 -0.0852 0.01112 0.00338 -0.0211 0.6153 0.0215 -2.250 -0.0554 0.01087 0.00310 -0.0215 0.6105 0.0233 -2.000 -0.0256 0.01068 0.00290 -0.0219 0.6050 0.0255 -1.750 0.0043 0.01050 0.00270 -0.0223 0.5994 0.0284 -1.500 0.0342 0.01037 0.00254 -0.0227 0.5945 0.0334 -1.250 0.0642 0.01018 0.00239 -0.0231 0.5888 0.0453 -1.000 0.0941 0.00999 0.00225 -0.0236 0.5826 0.0749 -0.750 0.1242 0.00931 0.00210 -0.0246 0.5770 0.2343 -0.500 0.1541 0.00832 0.00200 -0.0258 0.5706 0.5010 -0.250 0.1837 0.00803 0.00198 -0.0263 0.5642 0.5965 0.000 0.2129 0.00772 0.00198 -0.0266 0.5578 0.6851 0.250 0.2414 0.00755 0.00203 -0.0266 0.5511 0.7586 0.500 0.2694 0.00746 0.00204 -0.0265 0.5450 0.8034 0.750 0.2968 0.00740 0.00207 -0.0262 0.5382 0.8386 1.000 0.3245 0.00741 0.00209 -0.0259 0.5315 0.8624 1.250 0.3517 0.00741 0.00212 -0.0256 0.5247 0.8850 1.500 0.3787 0.00745 0.00214 -0.0253 0.5178 0.9054 1.750 0.4069 0.00749 0.00216 -0.0253 0.5104 0.9222 2.000 0.4351 0.00755 0.00217 -0.0253 0.5016 0.9350 2.250 0.4627 0.00757 0.00218 -0.0252 0.4923 0.9474 2.500 0.4908 0.00758 0.00216 -0.0251 0.4832 0.9639 2.750 0.5234 0.00761 0.00217 -0.0262 0.4742 0.9860 3.000 0.5546 0.00771 0.00222 -0.0270 0.4652 1.0000 3.250 0.5849 0.00784 0.00230 -0.0277 0.4550 1.0000 3.500 0.6151 0.00796 0.00239 -0.0283 0.4458 1.0000 3.750 0.6452 0.00810 0.00249 -0.0289 0.4363 1.0000 4.000 0.6753 0.00825 0.00260 -0.0296 0.4237 1.0000 4.250 0.7052 0.00842 0.00272 -0.0302 0.4105 1.0000 4.500 0.7351 0.00859 0.00286 -0.0308 0.3987 1.0000 4.750 0.7648 0.00879 0.00301 -0.0315 0.3877 1.0000 5.000 0.7945 0.00899 0.00318 -0.0321 0.3785 1.0000 5.250 0.8241 0.00916 0.00336 -0.0326 0.3698 1.0000 5.500 0.8535 0.00938 0.00355 -0.0332 0.3591 1.0000 5.750 0.8828 0.00962 0.00375 -0.0338 0.3428 1.0000 6.000 0.9120 0.00987 0.00398 -0.0344 0.3273 1.0000 6.250 0.9410 0.01014 0.00421 -0.0350 0.3128 1.0000 6.500 0.9697 0.01046 0.00448 -0.0356 0.2934 1.0000 6.750 0.9980 0.01088 0.00481 -0.0362 0.2700 1.0000 7.000 1.0256 0.01141 0.00520 -0.0368 0.2397 1.0000 7.250 1.0518 0.01223 0.00577 -0.0375 0.1933 1.0000 7.500 1.0779 0.01294 0.00633 -0.0380 0.1651 1.0000 7.750 1.1037 0.01362 0.00688 -0.0384 0.1363 1.0000 8.000 1.1295 0.01421 0.00739 -0.0388 0.1182 1.0000 8.250 1.1543 0.01491 0.00798 -0.0391 0.0962 1.0000 8.500 1.1788 0.01558 0.00859 -0.0393 0.0812 1.0000 8.750 1.2031 0.01621 0.00919 -0.0394 0.0711 1.0000 9.000 1.2269 0.01686 0.00982 -0.0395 0.0629 1.0000 9.250 1.2506 0.01744 0.01043 -0.0396 0.0572 1.0000 9.500 1.2729 0.01815 0.01113 -0.0395 0.0514 1.0000 9.750 1.2960 0.01871 0.01175 -0.0395 0.0470 1.0000 10.000 1.3167 0.01947 0.01250 -0.0393 0.0411 1.0000 10.250 1.3365 0.02025 0.01331 -0.0390 0.0359 1.0000 10.500 1.3548 0.02113 0.01420 -0.0386 0.0319 1.0000 10.750 1.3708 0.02213 0.01522 -0.0382 0.0287 1.0000 11.000 1.3827 0.02318 0.01633 -0.0371 0.0266 1.0000 11.250 1.3945 0.02429 0.01751 -0.0361 0.0249 1.0000 11.500 1.4050 0.02560 0.01887 -0.0353 0.0234 1.0000 11.750 1.4136 0.02716 0.02048 -0.0345 0.0220 1.0000 12.000 1.4241 0.02860 0.02201 -0.0340 0.0212 1.0000 12.250 1.4338 0.03019 0.02368 -0.0336 0.0203 1.0000 12.500 1.4421 0.03195 0.02552 -0.0333 0.0194 1.0000 12.750 1.4488 0.03394 0.02758 -0.0330 0.0187 1.0000 13.000 1.4534 0.03619 0.02990 -0.0328 0.0180 1.0000 13.250 1.4563 0.03868 0.03248 -0.0328 0.0173 1.0000 13.500 1.4618 0.04090 0.03480 -0.0327 0.0169 1.0000 13.750 1.4659 0.04329 0.03730 -0.0327 0.0164 1.0000 14.000 1.4687 0.04586 0.03996 -0.0328 0.0159 1.0000 14.250 1.4702 0.04858 0.04278 -0.0329 0.0154 1.0000 14.500 1.4702 0.05152 0.04581 -0.0331 0.0150 1.0000 14.750 1.4688 0.05469 0.04907 -0.0334 0.0146 1.0000 15.000 1.4659 0.05813 0.05259 -0.0339 0.0142 1.0000 15.250 1.4610 0.06194 0.05650 -0.0346 0.0139 1.0000 15.500 1.4574 0.06567 0.06033 -0.0353 0.0136 1.0000 15.750 1.4557 0.06920 0.06397 -0.0360 0.0133 1.0000 16.000 1.4533 0.07293 0.06783 -0.0369 0.0130 1.0000 16.250 1.4501 0.07683 0.07184 -0.0379 0.0126 1.0000 16.500 1.4461 0.08088 0.07600 -0.0390 0.0123 1.0000 16.750 1.4416 0.08508 0.08030 -0.0403 0.0120 1.0000 17.000 1.4361 0.08952 0.08484 -0.0416 0.0117 1.0000 17.250 1.4295 0.09417 0.08959 -0.0432 0.0114 1.0000 17.500 1.4218 0.09904 0.09456 -0.0448 0.0112 1.0000 17.750 1.4129 0.10420 0.09981 -0.0467 0.0110 1.0000 18.000 1.4027 0.10965 0.10536 -0.0488 0.0108 1.0000