XFOIL Version 6.96 Calculated polar for: BOEING-VERTOL VR-14 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5695 0.09193 0.09044 0.0092 1.0000 0.0083 -8.250 -0.5686 0.08750 0.08604 0.0059 1.0000 0.0083 -8.000 -0.5695 0.08264 0.08120 0.0010 1.0000 0.0084 -7.750 -0.5678 0.07735 0.07589 -0.0047 1.0000 0.0085 -7.500 -0.5611 0.07192 0.07043 -0.0098 1.0000 0.0086 -7.250 -0.5522 0.06654 0.06499 -0.0140 1.0000 0.0088 -7.000 -0.5411 0.06119 0.05955 -0.0175 1.0000 0.0090 -6.750 -0.5279 0.05582 0.05407 -0.0201 1.0000 0.0094 -6.500 -0.5652 0.01897 0.01510 -0.0178 0.9847 0.0050 -6.250 -0.5443 0.01616 0.01182 -0.0166 0.9763 0.0049 -6.000 -0.5249 0.01399 0.00923 -0.0148 0.9680 0.0050 -5.750 -0.5053 0.01251 0.00747 -0.0129 0.9596 0.0052 -5.500 -0.4830 0.01174 0.00658 -0.0116 0.9525 0.0056 -5.250 -0.4596 0.01129 0.00605 -0.0104 0.9455 0.0060 -5.000 -0.4352 0.01087 0.00556 -0.0095 0.9388 0.0066 -4.750 -0.4107 0.01053 0.00514 -0.0086 0.9316 0.0072 -4.500 -0.3867 0.00985 0.00436 -0.0076 0.9244 0.0082 -4.250 -0.3613 0.00958 0.00405 -0.0070 0.9171 0.0094 -4.000 -0.3355 0.00921 0.00365 -0.0063 0.9101 0.0118 -3.750 -0.3084 0.00922 0.00368 -0.0060 0.9030 0.0143 -3.500 -0.2814 0.00913 0.00362 -0.0058 0.8949 0.0168 -3.250 -0.2545 0.00923 0.00370 -0.0054 0.8848 0.0190 -3.000 -0.2281 0.00901 0.00342 -0.0049 0.8734 0.0207 -2.750 -0.2017 0.00870 0.00310 -0.0045 0.8623 0.0233 -2.500 -0.1743 0.00863 0.00301 -0.0043 0.8512 0.0258 -2.250 -0.1468 0.00858 0.00291 -0.0041 0.8391 0.0273 -2.000 -0.1210 0.00810 0.00232 -0.0035 0.8270 0.0300 -1.750 -0.0938 0.00790 0.00209 -0.0032 0.8149 0.0327 -1.500 -0.0663 0.00776 0.00189 -0.0030 0.8032 0.0347 -1.250 -0.0386 0.00763 0.00172 -0.0029 0.7925 0.0363 -1.000 -0.0108 0.00754 0.00158 -0.0027 0.7824 0.0377 -0.750 0.0169 0.00740 0.00137 -0.0025 0.7718 0.0417 -0.500 0.0441 0.00715 0.00122 -0.0023 0.7598 0.0782 -0.250 0.0659 0.00601 0.00107 -0.0016 0.7483 0.4112 0.000 0.0845 0.00490 0.00097 0.0001 0.7350 0.7245 0.250 0.1097 0.00431 0.00105 0.0012 0.7185 0.9392 0.500 0.1634 0.00458 0.00122 -0.0042 0.6891 0.9797 0.750 0.2190 0.00495 0.00140 -0.0102 0.6452 0.9946 1.000 0.2635 0.00525 0.00142 -0.0140 0.5778 0.9982 1.250 0.3013 0.00568 0.00147 -0.0165 0.4847 1.0000 1.500 0.3300 0.00603 0.00151 -0.0169 0.4105 1.0000 1.750 0.3582 0.00637 0.00156 -0.0173 0.3443 1.0000 2.000 0.3858 0.00659 0.00161 -0.0174 0.3048 1.0000 2.250 0.4129 0.00678 0.00166 -0.0174 0.2769 1.0000 2.500 0.4396 0.00696 0.00172 -0.0173 0.2538 1.0000 2.750 0.4660 0.00710 0.00179 -0.0171 0.2359 1.0000 3.000 0.4923 0.00724 0.00185 -0.0169 0.2217 1.0000 3.250 0.5185 0.00738 0.00193 -0.0166 0.2097 1.0000 3.500 0.5447 0.00752 0.00201 -0.0163 0.1989 1.0000 3.750 0.5708 0.00764 0.00211 -0.0160 0.1895 1.0000 4.000 0.5968 0.00779 0.00222 -0.0157 0.1804 1.0000 4.250 0.6227 0.00794 0.00233 -0.0154 0.1717 1.0000 4.500 0.6486 0.00808 0.00246 -0.0151 0.1635 1.0000 4.750 0.6743 0.00827 0.00260 -0.0147 0.1550 1.0000 5.000 0.7001 0.00841 0.00273 -0.0144 0.1492 1.0000 5.250 0.7256 0.00861 0.00290 -0.0140 0.1415 1.0000 5.500 0.7513 0.00875 0.00305 -0.0136 0.1357 1.0000 5.750 0.7767 0.00897 0.00323 -0.0133 0.1286 1.0000 6.000 0.8022 0.00912 0.00339 -0.0129 0.1237 1.0000 6.250 0.8275 0.00932 0.00358 -0.0125 0.1176 1.0000 6.500 0.8528 0.00952 0.00378 -0.0121 0.1118 1.0000 6.750 0.8780 0.00972 0.00398 -0.0117 0.1058 1.0000 7.000 0.9030 0.00996 0.00421 -0.0112 0.0995 1.0000 7.250 0.9279 0.01018 0.00443 -0.0108 0.0925 1.0000 7.500 0.9526 0.01045 0.00469 -0.0104 0.0830 1.0000 7.750 0.9766 0.01082 0.00499 -0.0098 0.0698 1.0000 8.000 1.0003 0.01123 0.00534 -0.0093 0.0592 1.0000 8.250 1.0239 0.01165 0.00573 -0.0087 0.0516 1.0000 8.500 1.0475 0.01204 0.00612 -0.0081 0.0463 1.0000 8.750 1.0709 0.01245 0.00655 -0.0075 0.0398 1.0000 9.000 1.0938 0.01293 0.00699 -0.0069 0.0330 1.0000 9.250 1.1168 0.01337 0.00743 -0.0062 0.0287 1.0000 9.500 1.1389 0.01393 0.00797 -0.0055 0.0249 1.0000 9.750 1.1613 0.01443 0.00853 -0.0048 0.0227 1.0000 10.000 1.1843 0.01481 0.00898 -0.0041 0.0215 1.0000 10.250 1.2065 0.01528 0.00949 -0.0034 0.0199 1.0000 10.500 1.2277 0.01589 0.01012 -0.0026 0.0181 1.0000 10.750 1.2477 0.01664 0.01095 -0.0016 0.0163 1.0000 11.000 1.2704 0.01700 0.01136 -0.0010 0.0158 1.0000 11.250 1.2922 0.01745 0.01188 -0.0004 0.0150 1.0000 11.500 1.3134 0.01797 0.01244 0.0004 0.0141 1.0000 11.750 1.3338 0.01857 0.01309 0.0011 0.0131 1.0000 12.000 1.3520 0.01940 0.01398 0.0022 0.0118 1.0000 12.250 1.3717 0.02001 0.01467 0.0030 0.0112 1.0000 12.500 1.3923 0.02050 0.01521 0.0038 0.0108 1.0000 12.750 1.4120 0.02104 0.01581 0.0046 0.0101 1.0000 13.000 1.4307 0.02166 0.01646 0.0054 0.0092 1.0000 13.250 1.4469 0.02250 0.01734 0.0066 0.0081 1.0000 13.500 1.4640 0.02317 0.01810 0.0076 0.0073 1.0000 13.750 1.4784 0.02404 0.01901 0.0089 0.0058 1.0000 14.000 1.4874 0.02518 0.02020 0.0108 0.0040 1.0000 14.250 1.4900 0.02658 0.02167 0.0134 0.0028 1.0000 14.500 1.4907 0.02824 0.02343 0.0158 0.0022 1.0000 14.750 1.4916 0.03003 0.02535 0.0176 0.0018 1.0000 15.000 1.4931 0.03189 0.02734 0.0190 0.0017 1.0000 15.250 1.4925 0.03409 0.02967 0.0201 0.0016 1.0000 15.500 1.4899 0.03668 0.03241 0.0206 0.0015 1.0000 15.750 1.4850 0.03977 0.03564 0.0206 0.0015 1.0000 16.000 1.4769 0.04352 0.03953 0.0199 0.0015 1.0000 16.250 1.4647 0.04823 0.04441 0.0181 0.0014 1.0000 16.500 1.4478 0.05426 0.05062 0.0151 0.0014 1.0000 16.750 1.4236 0.06246 0.05902 0.0101 0.0014 1.0000 17.000 1.3870 0.07395 0.07073 0.0030 0.0015 1.0000 17.250 1.3381 0.08741 0.08439 -0.0041 0.0016 1.0000 17.500 1.2847 0.10095 0.09810 -0.0109 0.0018 1.0000