XFOIL Version 6.96 Calculated polar for: NACA M24 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.2239 0.08768 0.08449 -0.0106 0.6241 0.0249 -8.000 -0.2197 0.08453 0.08131 -0.0114 0.6205 0.0251 -7.750 -0.2163 0.08133 0.07808 -0.0124 0.6171 0.0255 -7.500 -0.2140 0.07796 0.07473 -0.0138 0.6137 0.0258 -7.250 -0.2132 0.07448 0.07127 -0.0157 0.6102 0.0262 -7.000 -0.2139 0.07097 0.06773 -0.0176 0.6069 0.0266 -6.750 -0.2145 0.06765 0.06438 -0.0186 0.6037 0.0271 -6.500 -0.2098 0.06388 0.06056 -0.0206 0.6006 0.0279 -6.250 -0.2026 0.05894 0.05549 -0.0264 0.5980 0.0288 -6.000 -0.1906 0.05459 0.05104 -0.0285 0.5947 0.0289 -5.750 -0.1850 0.04995 0.04639 -0.0280 0.5913 0.0292 -5.500 -0.1726 0.04696 0.04334 -0.0278 0.5877 0.0295 -5.250 -0.1585 0.04419 0.04051 -0.0279 0.5840 0.0298 -5.000 -0.1429 0.04134 0.03762 -0.0282 0.5802 0.0302 -4.750 -0.1261 0.03850 0.03472 -0.0286 0.5763 0.0309 -4.500 -0.1081 0.03564 0.03175 -0.0291 0.5728 0.0317 -4.250 -0.0880 0.03269 0.02863 -0.0296 0.5695 0.0333 -4.000 -0.0635 0.02787 0.02349 -0.0302 0.5668 0.0347 -3.750 -0.0474 0.02550 0.02111 -0.0299 0.5629 0.0352 -3.500 -0.0280 0.02367 0.01923 -0.0296 0.5589 0.0356 -3.250 -0.0074 0.02193 0.01738 -0.0294 0.5553 0.0363 -3.000 0.0144 0.02017 0.01548 -0.0291 0.5518 0.0374 -2.750 0.0464 0.01815 0.01307 -0.0283 0.5485 0.0411 -2.500 0.0620 0.01515 0.00999 -0.0276 0.5450 0.0420 -2.250 0.0842 0.01405 0.00882 -0.0274 0.5411 0.0426 -2.000 0.1074 0.01306 0.00770 -0.0271 0.5376 0.0436 -1.750 0.1321 0.01202 0.00656 -0.0268 0.5340 0.0456 -1.500 0.1577 0.01024 0.00442 -0.0256 0.5307 0.0503 -1.250 0.1822 0.00958 0.00372 -0.0255 0.5266 0.0514 -1.000 0.2075 0.00897 0.00299 -0.0253 0.5230 0.0533 -0.750 0.2342 0.00800 0.00164 -0.0244 0.5198 0.0600 -0.500 0.2601 0.00747 0.00111 -0.0245 0.5160 0.0614 -0.250 0.2966 0.01537 0.00779 -0.0224 0.5168 0.0418 0.000 0.3256 0.01503 0.00737 -0.0225 0.5127 0.0412 0.250 0.3546 0.01429 0.00651 -0.0226 0.5087 0.0413 0.500 0.3833 0.01386 0.00595 -0.0227 0.5048 0.0411 0.750 0.4122 0.01318 0.00526 -0.0229 0.5012 0.0409 1.000 0.4405 0.01278 0.00484 -0.0229 0.4972 0.0411 1.250 0.4675 0.01225 0.00427 -0.0227 0.4934 0.0418 1.500 0.4941 0.01199 0.00397 -0.0225 0.4896 0.0428 1.750 0.5214 0.01179 0.00381 -0.0224 0.4857 0.0441 2.000 0.5488 0.01165 0.00369 -0.0224 0.4816 0.0456 2.250 0.5763 0.01158 0.00361 -0.0223 0.4778 0.0481 2.500 0.6032 0.01152 0.00351 -0.0222 0.4741 0.0512 2.750 0.6308 0.01146 0.00349 -0.0223 0.4704 0.0573 3.000 0.6576 0.01130 0.00353 -0.0221 0.4664 0.1117 3.250 0.6842 0.01119 0.00360 -0.0221 0.4624 0.1943 3.500 0.7083 0.00974 0.00397 -0.0213 0.4587 0.9532 3.750 0.7840 0.01035 0.00456 -0.0315 0.4535 0.9786 4.000 0.8898 0.01078 0.00491 -0.0484 0.4473 0.9959 4.250 0.9405 0.01089 0.00493 -0.0537 0.4428 1.0000 4.500 0.9670 0.01096 0.00501 -0.0537 0.4391 1.0000 4.750 0.9935 0.01102 0.00509 -0.0537 0.4350 1.0000 5.000 1.0197 0.01111 0.00515 -0.0537 0.4311 1.0000 5.250 1.0459 0.01127 0.00526 -0.0537 0.4273 1.0000 5.500 1.0721 0.01137 0.00539 -0.0537 0.4239 1.0000 5.750 1.0981 0.01147 0.00551 -0.0536 0.4201 1.0000 6.000 1.1240 0.01158 0.00563 -0.0536 0.4165 1.0000 6.250 1.1496 0.01176 0.00577 -0.0535 0.4129 1.0000 6.500 1.1752 0.01191 0.00595 -0.0534 0.4092 1.0000 6.750 1.2006 0.01201 0.00610 -0.0533 0.4048 1.0000 7.000 1.2256 0.01214 0.00623 -0.0532 0.3995 1.0000 7.250 1.2503 0.01232 0.00641 -0.0530 0.3941 1.0000 7.500 1.2751 0.01244 0.00659 -0.0528 0.3893 1.0000 7.750 1.2993 0.01261 0.00677 -0.0525 0.3843 1.0000 8.000 1.3229 0.01279 0.00697 -0.0522 0.3776 1.0000 8.250 1.3466 0.01295 0.00716 -0.0519 0.3703 1.0000 8.500 1.3694 0.01320 0.00740 -0.0514 0.3641 1.0000 8.750 1.3926 0.01337 0.00765 -0.0511 0.3575 1.0000 9.000 1.4142 0.01366 0.00793 -0.0505 0.3487 1.0000 9.250 1.4357 0.01393 0.00822 -0.0499 0.3386 1.0000 9.500 1.4562 0.01424 0.00856 -0.0491 0.3276 1.0000 9.750 1.4746 0.01469 0.00899 -0.0481 0.3128 1.0000 10.000 1.4889 0.01536 0.00958 -0.0466 0.2921 1.0000 10.250 1.4937 0.01651 0.01054 -0.0439 0.2551 1.0000 10.500 1.4757 0.01855 0.01228 -0.0381 0.2063 1.0000 10.750 1.4477 0.02023 0.01391 -0.0306 0.1892 1.0000 11.000 1.4207 0.02282 0.01639 -0.0250 0.1661 1.0000 11.250 1.3954 0.02618 0.01962 -0.0211 0.1391 1.0000 11.500 1.3675 0.03038 0.02368 -0.0182 0.1050 1.0000 11.750 1.3425 0.03478 0.02796 -0.0162 0.0801 1.0000 12.000 1.3213 0.03910 0.03222 -0.0147 0.0571 1.0000 12.250 1.2984 0.04377 0.03680 -0.0135 0.0360 1.0000 12.500 1.2875 0.04744 0.04048 -0.0128 0.0293 1.0000 12.750 1.2812 0.05082 0.04391 -0.0124 0.0262 1.0000 13.000 1.2794 0.05378 0.04695 -0.0122 0.0248 1.0000 13.250 1.2765 0.05694 0.05019 -0.0120 0.0238 1.0000 13.500 1.2724 0.06031 0.05363 -0.0119 0.0228 1.0000 13.750 1.2664 0.06394 0.05735 -0.0119 0.0219 1.0000 14.000 1.2608 0.06762 0.06112 -0.0120 0.0213 1.0000 14.250 1.2587 0.07094 0.06452 -0.0121 0.0209 1.0000 14.500 1.2556 0.07439 0.06806 -0.0123 0.0205 1.0000 14.750 1.2521 0.07794 0.07169 -0.0126 0.0200 1.0000 15.000 1.2480 0.08163 0.07545 -0.0130 0.0195 1.0000 15.250 1.2438 0.08536 0.07925 -0.0134 0.0191 1.0000 15.500 1.2389 0.08921 0.08318 -0.0138 0.0186 1.0000 15.750 1.2328 0.09327 0.08731 -0.0144 0.0182 1.0000 16.000 1.2254 0.09753 0.09163 -0.0150 0.0178 1.0000