XFOIL Version 6.96 Calculated polar for: BOEING VERTOL V43012-1.58 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.4277 0.08857 0.08688 -0.0258 1.0000 0.0095 -10.000 -0.4335 0.08375 0.08208 -0.0283 1.0000 0.0096 -9.750 -0.4387 0.07925 0.07759 -0.0310 1.0000 0.0097 -9.500 -0.4606 0.07218 0.07054 -0.0378 1.0000 0.0099 -9.000 -0.5226 0.05403 0.05199 -0.0449 0.9791 0.0111 -8.750 -0.5044 0.05137 0.04924 -0.0466 0.9734 0.0112 -8.500 -0.4853 0.04802 0.04575 -0.0486 0.9680 0.0113 -8.000 -0.4344 0.04244 0.03991 -0.0531 0.9476 0.0117 -7.500 -0.4036 0.03401 0.03081 -0.0525 0.8896 0.0130 -7.250 -0.3980 0.03037 0.02671 -0.0490 0.8428 0.0136 -6.750 -0.3890 0.01890 0.01400 -0.0407 0.7799 0.0161 -6.500 -0.3687 0.01831 0.01321 -0.0392 0.7493 0.0162 -6.250 -0.3472 0.01783 0.01257 -0.0380 0.7217 0.0163 -5.750 -0.3034 0.01684 0.01119 -0.0355 0.6534 0.0167 -5.500 -0.2805 0.01622 0.01039 -0.0344 0.6265 0.0169 -5.000 -0.2335 0.01483 0.00860 -0.0324 0.5750 0.0175 -4.750 -0.2092 0.01420 0.00778 -0.0315 0.5523 0.0180 -4.500 -0.1844 0.01364 0.00703 -0.0307 0.5349 0.0184 -4.250 -0.1592 0.01323 0.00648 -0.0299 0.5184 0.0186 -4.000 -0.1339 0.01294 0.00606 -0.0292 0.5002 0.0188 -3.750 -0.1099 0.01242 0.00542 -0.0283 0.4729 0.0189 -3.500 -0.0865 0.01216 0.00499 -0.0273 0.4305 0.0191 -3.250 -0.0623 0.01194 0.00467 -0.0265 0.4096 0.0193 -3.000 -0.0376 0.01171 0.00438 -0.0257 0.3956 0.0195 -2.750 -0.0127 0.01150 0.00412 -0.0249 0.3830 0.0197 -2.500 0.0122 0.01133 0.00389 -0.0242 0.3693 0.0200 -2.250 0.0370 0.01118 0.00366 -0.0234 0.3507 0.0203 -2.000 0.0613 0.01109 0.00346 -0.0226 0.3249 0.0206 -1.750 0.0855 0.01099 0.00325 -0.0217 0.3012 0.0209 -1.500 0.1101 0.01091 0.00308 -0.0208 0.2841 0.0212 -1.250 0.1350 0.01082 0.00292 -0.0201 0.2730 0.0214 -1.000 0.1605 0.01073 0.00279 -0.0194 0.2662 0.0216 -0.750 0.1861 0.01066 0.00268 -0.0188 0.2600 0.0218 -0.500 0.2116 0.01059 0.00258 -0.0182 0.2541 0.0219 -0.250 0.2369 0.01044 0.00241 -0.0175 0.2492 0.0223 0.000 0.2625 0.01037 0.00232 -0.0169 0.2433 0.0226 0.250 0.2882 0.01034 0.00226 -0.0163 0.2372 0.0229 0.500 0.3144 0.01030 0.00221 -0.0158 0.2325 0.0233 0.750 0.3405 0.01029 0.00218 -0.0153 0.2257 0.0240 1.000 0.3666 0.01030 0.00216 -0.0148 0.2205 0.0245 1.250 0.3929 0.01030 0.00214 -0.0144 0.2152 0.0249 1.500 0.4190 0.01033 0.00214 -0.0139 0.2094 0.0253 1.750 0.4452 0.01035 0.00214 -0.0134 0.2052 0.0260 2.000 0.4715 0.01037 0.00216 -0.0130 0.2018 0.0271 2.250 0.4976 0.01042 0.00219 -0.0126 0.1979 0.0283 2.500 0.5237 0.01048 0.00223 -0.0121 0.1942 0.0306 2.750 0.5496 0.01051 0.00231 -0.0116 0.1909 0.0558 3.000 0.5759 0.01054 0.00238 -0.0113 0.1894 0.0667 3.250 0.6020 0.01057 0.00245 -0.0108 0.1874 0.0910 3.500 0.6133 0.00944 0.00249 -0.0079 0.1858 0.5857 3.750 0.6308 0.00907 0.00256 -0.0057 0.1840 0.7286 4.000 0.6457 0.00876 0.00269 -0.0028 0.1819 0.8647 4.250 0.6806 0.00878 0.00291 -0.0041 0.1793 0.9385 4.500 0.7309 0.00902 0.00314 -0.0090 0.1757 0.9625 4.750 0.7706 0.00918 0.00330 -0.0116 0.1746 0.9719 5.000 0.8057 0.00932 0.00344 -0.0132 0.1728 0.9751 5.250 0.8382 0.00948 0.00359 -0.0142 0.1706 0.9801 5.500 0.8733 0.00967 0.00376 -0.0159 0.1680 0.9849 5.750 0.9065 0.00985 0.00392 -0.0171 0.1649 0.9869 6.000 0.9373 0.01004 0.00408 -0.0179 0.1617 0.9889 6.250 0.9676 0.01019 0.00424 -0.0186 0.1597 0.9909 6.500 0.9970 0.01034 0.00439 -0.0191 0.1566 0.9929 6.750 1.0275 0.01052 0.00455 -0.0198 0.1527 0.9945 7.000 1.0588 0.01074 0.00474 -0.0208 0.1483 0.9961 7.250 1.0902 0.01092 0.00492 -0.0218 0.1451 0.9976 7.500 1.1215 0.01112 0.00511 -0.0228 0.1407 0.9990 7.750 1.1521 0.01137 0.00533 -0.0237 0.1358 1.0000 8.000 1.1720 0.01157 0.00553 -0.0222 0.1325 1.0000 8.250 1.1915 0.01178 0.00574 -0.0207 0.1291 1.0000 8.500 1.2107 0.01203 0.00597 -0.0192 0.1256 1.0000 8.750 1.2299 0.01228 0.00622 -0.0176 0.1224 1.0000 9.000 1.2498 0.01249 0.00646 -0.0162 0.1208 1.0000 9.250 1.2695 0.01272 0.00671 -0.0148 0.1191 1.0000 9.500 1.2890 0.01297 0.00697 -0.0134 0.1174 1.0000 9.750 1.3080 0.01325 0.00725 -0.0119 0.1152 1.0000 10.000 1.3261 0.01358 0.00758 -0.0103 0.1119 1.0000 10.250 1.3453 0.01385 0.00788 -0.0089 0.1099 1.0000 10.500 1.3647 0.01411 0.00817 -0.0076 0.1088 1.0000 10.750 1.3838 0.01438 0.00847 -0.0062 0.1076 1.0000 11.000 1.4025 0.01466 0.00879 -0.0048 0.1066 1.0000 11.250 1.4208 0.01496 0.00913 -0.0033 0.1057 1.0000 11.500 1.4385 0.01529 0.00949 -0.0017 0.1046 1.0000 11.750 1.4536 0.01563 0.00985 0.0003 0.1032 1.0000 12.000 1.4670 0.01601 0.01026 0.0025 0.1013 1.0000 12.250 1.4809 0.01639 0.01068 0.0047 0.1000 1.0000 12.500 1.4952 0.01679 0.01113 0.0066 0.0990 1.0000 12.750 1.5121 0.01710 0.01150 0.0081 0.0983 1.0000 13.000 1.5286 0.01746 0.01191 0.0096 0.0971 1.0000 13.250 1.5442 0.01787 0.01237 0.0111 0.0948 1.0000 13.500 1.5585 0.01837 0.01290 0.0127 0.0926 1.0000 13.750 1.5704 0.01904 0.01358 0.0144 0.0891 1.0000 14.000 1.5851 0.01956 0.01416 0.0158 0.0871 1.0000 14.250 1.5990 0.02016 0.01478 0.0171 0.0823 1.0000 14.500 1.6085 0.02104 0.01566 0.0188 0.0762 1.0000 14.750 1.6124 0.02233 0.01689 0.0207 0.0656 1.0000 15.000 1.6027 0.02466 0.01914 0.0234 0.0518 1.0000 15.500 1.6024 0.02846 0.02302 0.0259 0.0433 1.0000 15.750 1.6028 0.03055 0.02518 0.0266 0.0412 1.0000 16.000 1.6024 0.03286 0.02756 0.0270 0.0392 1.0000 16.250 1.6023 0.03528 0.03007 0.0270 0.0374 1.0000 16.500 1.5986 0.03822 0.03310 0.0267 0.0358 1.0000 16.750 1.5900 0.04186 0.03683 0.0261 0.0342 1.0000 17.000 1.5817 0.04566 0.04073 0.0250 0.0327 1.0000 17.250 1.5715 0.04982 0.04500 0.0238 0.0317 1.0000 17.500 1.5567 0.05470 0.05000 0.0221 0.0309 1.0000 17.750 1.5377 0.06034 0.05577 0.0200 0.0304 1.0000 18.000 1.5124 0.06713 0.06271 0.0173 0.0298 1.0000 18.250 1.4834 0.07460 0.07033 0.0142 0.0298 1.0000 18.500 1.4503 0.08280 0.07869 0.0108 0.0298 1.0000 18.750 1.4170 0.09117 0.08722 0.0073 0.0300 1.0000