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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.5542 0.09191 0.08981 0.0015 1.0000 0.0144 -8.250 -0.5529 0.08693 0.08486 -0.0034 1.0000 0.0144 -8.000 -0.5518 0.08175 0.07967 -0.0086 1.0000 0.0144 -7.750 -0.5460 0.07638 0.07425 -0.0131 1.0000 0.0144 -7.500 -0.5387 0.07111 0.06891 -0.0166 1.0000 0.0144 -5.250 -0.4279 0.02928 0.02535 -0.0208 0.9929 0.0152 -5.000 -0.4089 0.01661 0.01113 -0.0176 0.9873 0.0108 -4.750 -0.3746 0.01598 0.01041 -0.0192 0.9841 0.0118 -4.500 -0.3431 0.01481 0.00905 -0.0199 0.9792 0.0130 -4.250 -0.3124 0.01372 0.00776 -0.0203 0.9736 0.0150 -4.000 -0.2829 0.01387 0.00798 -0.0208 0.9671 0.0172 -3.750 -0.2570 0.01326 0.00720 -0.0198 0.9591 0.0204 -3.500 -0.2339 0.01263 0.00657 -0.0188 0.9505 0.0236 -3.250 -0.2101 0.01263 0.00651 -0.0176 0.9431 0.0268 -3.000 -0.1874 0.01181 0.00566 -0.0164 0.9342 0.0308 -2.750 -0.1652 0.01138 0.00519 -0.0148 0.9247 0.0333 -2.500 -0.1438 0.01095 0.00469 -0.0130 0.9141 0.0356 -2.250 -0.1198 0.01074 0.00442 -0.0118 0.9026 0.0377 -2.000 -0.0976 0.00994 0.00355 -0.0103 0.8915 0.0409 -1.750 -0.0734 0.00957 0.00314 -0.0092 0.8807 0.0439 -1.500 -0.0485 0.00933 0.00283 -0.0083 0.8700 0.0474 -1.250 -0.0227 0.00911 0.00255 -0.0075 0.8585 0.0500 -1.000 0.0035 0.00881 0.00223 -0.0069 0.8472 0.0572 -0.750 0.0270 0.00800 0.00196 -0.0061 0.8369 0.2213 -0.500 0.0344 0.00581 0.00177 -0.0022 0.8272 0.7899 -0.250 0.0982 0.00576 0.00209 -0.0090 0.8167 0.9733 0.000 0.1695 0.00604 0.00225 -0.0181 0.8034 1.0000 0.250 0.1961 0.00603 0.00214 -0.0177 0.7886 1.0000 0.500 0.2227 0.00605 0.00204 -0.0174 0.7719 1.0000 0.750 0.2497 0.00606 0.00197 -0.0171 0.7534 1.0000 1.000 0.2767 0.00609 0.00190 -0.0169 0.7317 1.0000 1.250 0.3037 0.00614 0.00184 -0.0166 0.7045 1.0000 1.500 0.3307 0.00624 0.00178 -0.0164 0.6668 1.0000 1.750 0.3577 0.00643 0.00174 -0.0162 0.6082 1.0000 2.000 0.3846 0.00686 0.00175 -0.0162 0.5139 1.0000 2.250 0.4111 0.00740 0.00187 -0.0163 0.4189 1.0000 2.500 0.4372 0.00787 0.00199 -0.0163 0.3468 1.0000 2.750 0.4633 0.00820 0.00213 -0.0161 0.3063 1.0000 3.000 0.4892 0.00847 0.00226 -0.0159 0.2797 1.0000 3.250 0.5150 0.00870 0.00239 -0.0156 0.2591 1.0000 3.500 0.5406 0.00895 0.00253 -0.0153 0.2410 1.0000 3.750 0.5662 0.00918 0.00269 -0.0149 0.2255 1.0000 4.000 0.5918 0.00937 0.00284 -0.0146 0.2132 1.0000 4.250 0.6173 0.00957 0.00301 -0.0142 0.2028 1.0000 4.500 0.6427 0.00979 0.00321 -0.0138 0.1934 1.0000 4.750 0.6679 0.01003 0.00340 -0.0134 0.1839 1.0000 5.000 0.6933 0.01022 0.00359 -0.0130 0.1756 1.0000 5.250 0.7183 0.01050 0.00383 -0.0125 0.1678 1.0000 5.500 0.7436 0.01069 0.00405 -0.0121 0.1613 1.0000 5.750 0.7681 0.01101 0.00433 -0.0116 0.1545 1.0000 6.000 0.7935 0.01116 0.00454 -0.0112 0.1480 1.0000 6.250 0.8178 0.01150 0.00482 -0.0107 0.1408 1.0000 6.500 0.8432 0.01165 0.00505 -0.0102 0.1349 1.0000 6.750 0.8674 0.01198 0.00534 -0.0097 0.1275 1.0000 7.000 0.8926 0.01215 0.00558 -0.0093 0.1218 1.0000 7.250 0.9167 0.01248 0.00588 -0.0088 0.1137 1.0000 7.500 0.9417 0.01268 0.00615 -0.0083 0.1061 1.0000 7.750 0.9658 0.01299 0.00647 -0.0078 0.0974 1.0000 8.000 0.9896 0.01336 0.00682 -0.0073 0.0865 1.0000 8.250 1.0130 0.01377 0.00720 -0.0067 0.0743 1.0000 8.500 1.0356 0.01429 0.00767 -0.0060 0.0631 1.0000 8.750 1.0575 0.01491 0.00828 -0.0052 0.0544 1.0000 9.000 1.0794 0.01552 0.00896 -0.0044 0.0477 1.0000 9.250 1.0985 0.01649 0.00993 -0.0032 0.0408 1.0000 9.500 1.1214 0.01692 0.01046 -0.0026 0.0375 1.0000 9.750 1.1422 0.01762 0.01119 -0.0017 0.0339 1.0000 10.000 1.1594 0.01876 0.01242 -0.0003 0.0309 1.0000 10.250 1.1807 0.01933 0.01312 0.0005 0.0292 1.0000 10.500 1.2014 0.01994 0.01380 0.0013 0.0272 1.0000 10.750 1.2197 0.02080 0.01469 0.0023 0.0249 1.0000 11.000 1.2323 0.02227 0.01628 0.0041 0.0228 1.0000 11.250 1.2528 0.02279 0.01691 0.0048 0.0218 1.0000 11.500 1.2704 0.02360 0.01783 0.0059 0.0207 1.0000 11.750 1.2869 0.02446 0.01880 0.0071 0.0197 1.0000 12.000 1.3024 0.02534 0.01977 0.0083 0.0186 1.0000 12.250 1.3127 0.02663 0.02115 0.0100 0.0175 1.0000 12.500 1.3094 0.02876 0.02344 0.0132 0.0165 1.0000 12.750 1.3177 0.02986 0.02467 0.0151 0.0161 1.0000 13.000 1.3281 0.03086 0.02580 0.0165 0.0156 1.0000 13.250 1.3363 0.03210 0.02717 0.0178 0.0150 1.0000 13.500 1.3418 0.03364 0.02884 0.0190 0.0145 1.0000 13.750 1.3463 0.03538 0.03071 0.0199 0.0139 1.0000 14.000 1.3508 0.03724 0.03267 0.0204 0.0134 1.0000 14.250 1.3535 0.03943 0.03497 0.0206 0.0129 1.0000 14.500 1.3523 0.04224 0.03788 0.0202 0.0124 1.0000 14.750 1.3426 0.04634 0.04213 0.0192 0.0120 1.0000 15.000 1.3280 0.05162 0.04758 0.0170 0.0118 1.0000 15.250 1.3101 0.05809 0.05423 0.0135 0.0116 1.0000 15.500 1.2910 0.06544 0.06176 0.0091 0.0115 1.0000 15.750 1.2714 0.07328 0.06977 0.0045 0.0115 1.0000 16.000 1.2513 0.08120 0.07784 0.0001 0.0116 1.0000 16.250 1.2301 0.08922 0.08599 -0.0042 0.0116 1.0000 16.500 1.2088 0.09712 0.09401 -0.0082 0.0117 1.0000