XFOIL Version 6.96 Calculated polar for: SD7084 (9.6%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4358 0.11912 0.11395 -0.0192 1.0000 0.0522 -10.500 -0.4433 0.11583 0.11075 -0.0238 1.0000 0.0549 -10.250 -0.4460 0.11213 0.10710 -0.0270 1.0000 0.0552 -9.500 -0.4441 0.09338 0.08842 -0.0330 1.0000 0.0317 -9.250 -0.4420 0.08980 0.08488 -0.0332 1.0000 0.0310 -9.000 -0.4428 0.08582 0.08095 -0.0345 1.0000 0.0306 -8.750 -0.4453 0.08176 0.07695 -0.0362 1.0000 0.0303 -8.500 -0.4509 0.07749 0.07276 -0.0382 1.0000 0.0299 -8.250 -0.4623 0.07295 0.06830 -0.0407 1.0000 0.0296 -8.000 -0.4736 0.06843 0.06382 -0.0427 1.0000 0.0291 -7.750 -0.4849 0.06384 0.05921 -0.0436 1.0000 0.0288 -7.500 -0.4953 0.05956 0.05486 -0.0434 1.0000 0.0285 -7.250 -0.5046 0.05528 0.05044 -0.0425 1.0000 0.0282 -7.000 -0.5104 0.05121 0.04618 -0.0411 1.0000 0.0281 -6.750 -0.5128 0.04720 0.04191 -0.0395 1.0000 0.0280 -6.500 -0.5112 0.04349 0.03786 -0.0377 1.0000 0.0286 -6.250 -0.5059 0.04006 0.03402 -0.0359 1.0000 0.0296 -6.000 -0.4971 0.03692 0.03040 -0.0341 1.0000 0.0305 -5.750 -0.4854 0.03405 0.02703 -0.0323 1.0000 0.0309 -5.500 -0.4680 0.03137 0.02388 -0.0313 0.9991 0.0311 -5.250 -0.4368 0.02870 0.02064 -0.0326 0.9946 0.0315 -5.000 -0.4060 0.02638 0.01789 -0.0336 0.9901 0.0321 -4.750 -0.3742 0.02431 0.01558 -0.0348 0.9857 0.0333 -4.500 -0.3408 0.02311 0.01425 -0.0364 0.9812 0.0358 -4.250 -0.3085 0.02212 0.01304 -0.0374 0.9756 0.0393 -4.000 -0.2734 0.02095 0.01170 -0.0388 0.9712 0.0412 -3.750 -0.2420 0.02001 0.01061 -0.0395 0.9653 0.0431 -3.500 -0.2094 0.01898 0.00959 -0.0407 0.9596 0.0469 -3.250 -0.1757 0.01829 0.00880 -0.0419 0.9539 0.0533 -3.000 -0.1435 0.01759 0.00810 -0.0429 0.9469 0.0697 -2.750 -0.1077 0.01671 0.00747 -0.0447 0.9418 0.1178 -2.500 -0.0806 0.01569 0.00716 -0.0451 0.9335 0.2587 -2.250 -0.0479 0.01463 0.00700 -0.0464 0.9283 0.4750 -2.000 -0.0231 0.01404 0.00692 -0.0453 0.9191 0.6246 -1.750 0.0105 0.01358 0.00689 -0.0451 0.9138 0.7745 -1.500 0.0597 0.01341 0.00683 -0.0481 0.9081 0.8915 -1.250 0.1240 0.01330 0.00656 -0.0549 0.9046 0.9547 -1.000 0.1860 0.01314 0.00621 -0.0615 0.9004 0.9873 -0.750 0.2248 0.01302 0.00594 -0.0638 0.8891 1.0000 -0.500 0.2507 0.01291 0.00570 -0.0633 0.8754 1.0000 -0.250 0.2760 0.01281 0.00549 -0.0626 0.8611 1.0000 0.000 0.3012 0.01271 0.00528 -0.0618 0.8460 1.0000 0.250 0.3264 0.01262 0.00509 -0.0610 0.8303 1.0000 0.500 0.3499 0.01257 0.00495 -0.0598 0.8120 1.0000 0.750 0.3744 0.01251 0.00481 -0.0588 0.7936 1.0000 1.000 0.3998 0.01246 0.00465 -0.0579 0.7750 1.0000 1.250 0.4242 0.01245 0.00455 -0.0569 0.7543 1.0000 1.500 0.4493 0.01246 0.00445 -0.0559 0.7333 1.0000 1.750 0.4738 0.01251 0.00441 -0.0549 0.7104 1.0000 2.000 0.4985 0.01259 0.00437 -0.0540 0.6875 1.0000 2.250 0.5227 0.01272 0.00438 -0.0529 0.6633 1.0000 2.500 0.5467 0.01288 0.00443 -0.0519 0.6386 1.0000 2.750 0.5705 0.01306 0.00453 -0.0509 0.6138 1.0000 3.000 0.5943 0.01328 0.00463 -0.0499 0.5892 1.0000 3.250 0.6177 0.01352 0.00478 -0.0489 0.5643 1.0000 3.500 0.6411 0.01379 0.00495 -0.0479 0.5397 1.0000 3.750 0.6644 0.01408 0.00518 -0.0470 0.5158 1.0000 4.000 0.6876 0.01439 0.00540 -0.0460 0.4921 1.0000 4.250 0.7107 0.01471 0.00566 -0.0451 0.4689 1.0000 4.500 0.7336 0.01507 0.00594 -0.0441 0.4470 1.0000 4.750 0.7566 0.01542 0.00626 -0.0432 0.4252 1.0000 5.000 0.7793 0.01582 0.00662 -0.0423 0.4050 1.0000 5.250 0.8021 0.01620 0.00700 -0.0414 0.3851 1.0000 5.500 0.8247 0.01662 0.00739 -0.0405 0.3663 1.0000 5.750 0.8471 0.01707 0.00781 -0.0396 0.3491 1.0000 6.000 0.8697 0.01751 0.00827 -0.0387 0.3319 1.0000 6.250 0.8920 0.01797 0.00880 -0.0378 0.3157 1.0000 6.500 0.9141 0.01845 0.00932 -0.0369 0.3000 1.0000 6.750 0.9360 0.01895 0.00986 -0.0360 0.2850 1.0000 7.000 0.9576 0.01948 0.01043 -0.0350 0.2701 1.0000 7.250 0.9788 0.02002 0.01103 -0.0341 0.2554 1.0000 7.500 0.9996 0.02058 0.01170 -0.0330 0.2406 1.0000 7.750 1.0198 0.02116 0.01235 -0.0319 0.2255 1.0000 8.000 1.0394 0.02176 0.01303 -0.0308 0.2102 1.0000 8.250 1.0583 0.02239 0.01373 -0.0295 0.1938 1.0000 8.500 1.0767 0.02303 0.01448 -0.0283 0.1748 1.0000 8.750 1.0931 0.02377 0.01524 -0.0268 0.1544 1.0000 9.000 1.1085 0.02462 0.01612 -0.0254 0.1282 1.0000 9.250 1.1215 0.02573 0.01711 -0.0237 0.0961 1.0000 9.500 1.1304 0.02724 0.01841 -0.0217 0.0655 1.0000 9.750 1.1371 0.02892 0.01999 -0.0194 0.0453 1.0000 10.000 1.1406 0.03067 0.02173 -0.0166 0.0343 1.0000 10.250 1.1409 0.03248 0.02361 -0.0134 0.0290 1.0000 10.500 1.1418 0.03424 0.02553 -0.0106 0.0258 1.0000 10.750 1.1390 0.03634 0.02774 -0.0080 0.0237 1.0000 11.000 1.1340 0.03870 0.03023 -0.0056 0.0224 1.0000 11.250 1.1329 0.04092 0.03266 -0.0038 0.0211 1.0000 11.500 1.1310 0.04335 0.03528 -0.0024 0.0201 1.0000 11.750 1.1290 0.04594 0.03803 -0.0015 0.0190 1.0000 12.000 1.1256 0.04882 0.04105 -0.0010 0.0180 1.0000 12.250 1.1204 0.05208 0.04448 -0.0011 0.0170 1.0000 12.500 1.1142 0.05571 0.04825 -0.0015 0.0166 1.0000 12.750 1.1054 0.05988 0.05254 -0.0022 0.0161 1.0000 13.000 1.1012 0.06371 0.05653 -0.0030 0.0158 1.0000 13.250 1.0962 0.06785 0.06087 -0.0041 0.0154 1.0000 13.500 1.0908 0.07218 0.06539 -0.0054 0.0152 1.0000 13.750 1.0845 0.07681 0.07020 -0.0070 0.0151 1.0000 14.000 1.0769 0.08183 0.07542 -0.0090 0.0149 1.0000 14.250 1.0677 0.08737 0.08114 -0.0115 0.0148 1.0000 14.500 1.0579 0.09322 0.08718 -0.0143 0.0147 1.0000 14.750 1.0462 0.09969 0.09384 -0.0177 0.0146 1.0000 15.000 1.0339 0.10656 0.10088 -0.0214 0.0146 1.0000 15.250 1.0209 0.11386 0.10835 -0.0255 0.0147 1.0000 15.500 1.0064 0.12186 0.11650 -0.0301 0.0148 1.0000 15.750 0.9907 0.13055 0.12534 -0.0351 0.0149 1.0000 16.000 0.9748 0.13976 0.13468 -0.0405 0.0151 1.0000 16.250 0.9588 0.14953 0.14455 -0.0461 0.0153 1.0000