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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4008 0.09085 0.08849 -0.0254 1.0000 0.0129 -9.750 -0.4112 0.08476 0.08243 -0.0289 1.0000 0.0135 -9.500 -0.4190 0.07980 0.07750 -0.0318 1.0000 0.0135 -9.250 -0.4506 0.07165 0.06935 -0.0388 1.0000 0.0134 -9.000 -0.4441 0.07135 0.06907 -0.0372 1.0000 0.0137 -8.750 -0.4703 0.06831 0.06602 -0.0344 1.0000 0.0137 -8.500 -0.4668 0.06518 0.06285 -0.0356 0.9975 0.0138 -8.250 -0.4583 0.06104 0.05861 -0.0381 0.9897 0.0140 -8.000 -0.4460 0.05686 0.05429 -0.0405 0.9825 0.0143 -7.750 -0.4347 0.05269 0.04995 -0.0419 0.9742 0.0144 -7.500 -0.4186 0.04867 0.04575 -0.0432 0.9671 0.0148 -7.000 -0.3875 0.03839 0.03481 -0.0438 0.9474 0.0161 -6.750 -0.3584 0.03747 0.03385 -0.0453 0.9358 0.0165 -6.500 -0.3295 0.03532 0.03153 -0.0467 0.9186 0.0170 -6.250 -0.3052 0.03262 0.02855 -0.0467 0.8911 0.0174 -5.750 -0.2719 0.02524 0.02015 -0.0419 0.8237 0.0190 -5.500 -0.2515 0.02506 0.01979 -0.0407 0.7790 0.0193 -5.250 -0.2316 0.02438 0.01890 -0.0392 0.7482 0.0196 -5.000 -0.2121 0.02299 0.01722 -0.0374 0.7191 0.0200 -4.750 -0.1919 0.02120 0.01511 -0.0356 0.6903 0.0204 -4.500 -0.1709 0.01850 0.01196 -0.0336 0.6631 0.0210 -4.250 -0.1478 0.01684 0.00976 -0.0320 0.6357 0.0219 -4.000 -0.1244 0.01593 0.00869 -0.0310 0.6093 0.0222 -3.750 -0.1003 0.01532 0.00793 -0.0301 0.5853 0.0224 -3.500 -0.0758 0.01482 0.00731 -0.0293 0.5652 0.0227 -3.250 -0.0510 0.01435 0.00673 -0.0285 0.5478 0.0230 -3.000 -0.0262 0.01390 0.00617 -0.0277 0.5305 0.0233 -2.750 -0.0016 0.01351 0.00568 -0.0269 0.5116 0.0236 -2.500 0.0227 0.01322 0.00527 -0.0260 0.4879 0.0242 -2.250 0.0462 0.01299 0.00486 -0.0249 0.4501 0.0246 -2.000 0.0691 0.01281 0.00450 -0.0238 0.4194 0.0248 -1.750 0.0927 0.01262 0.00419 -0.0228 0.4012 0.0250 -1.500 0.1168 0.01247 0.00394 -0.0219 0.3855 0.0252 -1.250 0.1404 0.01228 0.00369 -0.0209 0.3686 0.0255 -1.000 0.1637 0.01208 0.00342 -0.0198 0.3488 0.0258 -0.750 0.1874 0.01198 0.00323 -0.0189 0.3262 0.0262 -0.250 0.2358 0.01189 0.00297 -0.0172 0.2906 0.0271 0.000 0.2606 0.01186 0.00288 -0.0165 0.2803 0.0278 0.500 0.3110 0.01183 0.00275 -0.0151 0.2653 0.0289 0.750 0.3362 0.01182 0.00271 -0.0145 0.2593 0.0295 1.000 0.3614 0.01184 0.00269 -0.0138 0.2538 0.0303 1.250 0.3872 0.01184 0.00268 -0.0133 0.2480 0.0313 1.500 0.4126 0.01189 0.00269 -0.0127 0.2416 0.0327 1.750 0.4381 0.01194 0.00273 -0.0121 0.2361 0.0358 2.000 0.4639 0.01196 0.00280 -0.0116 0.2305 0.0579 2.250 0.4894 0.01201 0.00286 -0.0111 0.2253 0.0734 2.500 0.5148 0.01208 0.00292 -0.0105 0.2210 0.0924 2.750 0.5229 0.01068 0.00291 -0.0070 0.2179 0.6175 3.000 0.5357 0.01016 0.00302 -0.0036 0.2143 0.7945 3.250 0.5650 0.01009 0.00324 -0.0036 0.2100 0.9004 3.500 0.6226 0.01037 0.00353 -0.0099 0.2048 0.9492 3.750 0.6686 0.01061 0.00375 -0.0137 0.2013 0.9668 4.000 0.7121 0.01087 0.00397 -0.0170 0.1976 0.9770 4.250 0.7451 0.01109 0.00415 -0.0181 0.1944 0.9832 4.500 0.7839 0.01133 0.00433 -0.0205 0.1910 0.9867 4.750 0.8195 0.01149 0.00450 -0.0223 0.1890 0.9902 5.000 0.8513 0.01166 0.00466 -0.0232 0.1866 0.9930 5.250 0.8828 0.01183 0.00482 -0.0241 0.1839 0.9951 5.500 0.9148 0.01201 0.00499 -0.0252 0.1811 0.9972 5.750 0.9462 0.01223 0.00519 -0.0262 0.1782 0.9991 6.000 0.9728 0.01246 0.00540 -0.0262 0.1755 1.0000 6.250 0.9933 0.01260 0.00557 -0.0248 0.1738 1.0000 6.500 1.0136 0.01276 0.00575 -0.0234 0.1717 1.0000 6.750 1.0338 0.01293 0.00595 -0.0219 0.1692 1.0000 7.000 1.0537 0.01313 0.00615 -0.0205 0.1664 1.0000 7.250 1.0732 0.01336 0.00637 -0.0190 0.1634 1.0000 7.500 1.0926 0.01360 0.00660 -0.0175 0.1605 1.0000 7.750 1.1132 0.01378 0.00683 -0.0162 0.1581 1.0000 8.000 1.1334 0.01399 0.00706 -0.0148 0.1550 1.0000 8.250 1.1533 0.01422 0.00730 -0.0134 0.1518 1.0000 8.500 1.1724 0.01449 0.00757 -0.0119 0.1486 1.0000 8.750 1.1920 0.01475 0.00785 -0.0105 0.1460 1.0000 9.000 1.2118 0.01500 0.00814 -0.0092 0.1432 1.0000 9.250 1.2310 0.01527 0.00844 -0.0078 0.1402 1.0000 9.500 1.2496 0.01558 0.00875 -0.0063 0.1374 1.0000 9.750 1.2674 0.01593 0.00911 -0.0047 0.1347 1.0000 10.000 1.2860 0.01623 0.00946 -0.0032 0.1329 1.0000 10.250 1.3038 0.01655 0.00983 -0.0016 0.1309 1.0000 10.500 1.3211 0.01690 0.01022 0.0000 0.1291 1.0000 10.750 1.3369 0.01727 0.01062 0.0019 0.1271 1.0000 11.000 1.3497 0.01769 0.01104 0.0043 0.1239 1.0000 11.250 1.3630 0.01809 0.01148 0.0065 0.1217 1.0000 11.500 1.3777 0.01848 0.01192 0.0084 0.1199 1.0000 11.750 1.3921 0.01890 0.01241 0.0103 0.1185 1.0000 12.000 1.4061 0.01937 0.01294 0.0122 0.1169 1.0000 12.250 1.4194 0.01990 0.01351 0.0140 0.1152 1.0000 12.500 1.4319 0.02050 0.01415 0.0158 0.1134 1.0000 12.750 1.4430 0.02119 0.01488 0.0177 0.1116 1.0000 13.000 1.4546 0.02189 0.01564 0.0194 0.1104 1.0000 13.250 1.4685 0.02250 0.01635 0.0207 0.1096 1.0000 13.500 1.4815 0.02319 0.01714 0.0220 0.1086 1.0000 13.750 1.4937 0.02396 0.01799 0.0233 0.1075 1.0000 14.000 1.5052 0.02481 0.01892 0.0245 0.1055 1.0000 14.250 1.5150 0.02580 0.01999 0.0257 0.1037 1.0000 14.500 1.5208 0.02714 0.02135 0.0269 0.1005 1.0000 14.750 1.5280 0.02846 0.02274 0.0278 0.0987 1.0000 15.000 1.5402 0.02947 0.02387 0.0284 0.0963 1.0000 15.250 1.5484 0.03084 0.02534 0.0289 0.0932 1.0000 15.500 1.5516 0.03274 0.02728 0.0293 0.0896 1.0000 15.750 1.5558 0.03464 0.02926 0.0296 0.0876 1.0000 16.000 1.5630 0.03633 0.03107 0.0297 0.0846 1.0000 16.250 1.5646 0.03867 0.03348 0.0295 0.0796 1.0000 16.500 1.5615 0.04162 0.03648 0.0290 0.0730 1.0000 16.750 1.5493 0.04577 0.04067 0.0280 0.0656 1.0000 17.000 1.5349 0.05035 0.04533 0.0266 0.0612 1.0000 17.250 1.5133 0.05606 0.05113 0.0246 0.0567 1.0000 17.750 1.4636 0.06920 0.06451 0.0194 0.0527 1.0000 18.000 1.4364 0.07636 0.07183 0.0164 0.0515 1.0000 18.250 1.3997 0.08513 0.08073 0.0127 0.0498 1.0000 18.500 1.3745 0.09228 0.08802 0.0096 0.0498 1.0000