XFOIL Version 6.96 Calculated polar for: NACA 2424 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0543 0.08077 0.07568 -0.0785 1.0000 0.0857 -19.500 -1.0587 0.07766 0.07248 -0.0791 1.0000 0.0867 -19.250 -1.0605 0.07506 0.06986 -0.0793 1.0000 0.0880 -19.000 -1.0641 0.07228 0.06709 -0.0796 1.0000 0.0894 -18.750 -1.0670 0.06957 0.06435 -0.0798 1.0000 0.0906 -18.500 -1.0709 0.06677 0.06151 -0.0800 1.0000 0.0919 -18.250 -1.0738 0.06413 0.05880 -0.0801 1.0000 0.0934 -18.000 -1.0762 0.06157 0.05614 -0.0801 1.0000 0.0945 -17.750 -1.0799 0.05916 0.05375 -0.0797 1.0000 0.0959 -17.500 -1.0848 0.05663 0.05120 -0.0793 1.0000 0.0972 -17.250 -1.0892 0.05419 0.04873 -0.0788 1.0000 0.0986 -17.000 -1.0917 0.05203 0.04652 -0.0781 1.0000 0.1001 -16.750 -1.0945 0.04992 0.04435 -0.0773 1.0000 0.1017 -16.500 -1.0977 0.04795 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0.00427 -0.0388 0.6062 0.4154 -1.500 0.0222 0.01088 0.00424 -0.0353 0.5982 0.4257 -1.250 0.0334 0.01083 0.00423 -0.0317 0.5900 0.4365 -1.000 0.0459 0.01082 0.00420 -0.0284 0.5819 0.4473 -0.750 0.0589 0.01080 0.00420 -0.0253 0.5743 0.4595 -0.500 0.0712 0.01077 0.00420 -0.0219 0.5668 0.4718 -0.250 0.0844 0.01078 0.00420 -0.0188 0.5595 0.4851 0.000 0.0979 0.01076 0.00423 -0.0157 0.5525 0.4985 0.500 0.1250 0.01075 0.00427 -0.0096 0.5382 0.5273 0.750 0.1404 0.01078 0.00431 -0.0069 0.5314 0.5425 1.000 0.1542 0.01077 0.00436 -0.0039 0.5248 0.5581 1.250 0.1677 0.01077 0.00441 -0.0009 0.5181 0.5735 1.500 0.1835 0.01085 0.00446 0.0017 0.5110 0.5893 1.750 0.1981 0.01083 0.00453 0.0045 0.5054 0.6055 2.000 0.2129 0.01084 0.00460 0.0072 0.4986 0.6211 2.500 0.2433 0.01094 0.00476 0.0125 0.4860 0.6541 2.750 0.2589 0.01096 0.00485 0.0151 0.4798 0.6710 3.250 0.2908 0.01110 0.00504 0.0199 0.4668 0.7073 3.500 0.3072 0.01112 0.00517 0.0223 0.4610 0.7265 3.750 0.3243 0.01117 0.00529 0.0244 0.4544 0.7469 4.000 0.3424 0.01128 0.00542 0.0263 0.4480 0.7693 4.250 0.3640 0.01133 0.00559 0.0276 0.4421 0.7927 4.500 0.3883 0.01142 0.00576 0.0281 0.4353 0.8170 4.750 0.4182 0.01158 0.00596 0.0275 0.4280 0.8418 5.000 0.4592 0.01172 0.00619 0.0245 0.4211 0.8650 5.250 0.5122 0.01194 0.00645 0.0190 0.4127 0.8840 5.500 0.5688 0.01228 0.00678 0.0126 0.4043 0.8984 5.750 0.6167 0.01257 0.00711 0.0083 0.3964 0.9111 6.000 0.6625 0.01303 0.00752 0.0042 0.3882 0.9204 6.250 0.6993 0.01341 0.00792 0.0021 0.3808 0.9299 6.500 0.7356 0.01387 0.00835 0.0001 0.3728 0.9366 6.750 0.7585 0.01438 0.00881 0.0007 0.3660 0.9476 7.000 0.7919 0.01479 0.00924 -0.0008 0.3589 0.9535 7.250 0.8149 0.01529 0.00970 -0.0003 0.3520 0.9632 7.500 0.8486 0.01577 0.01016 -0.0020 0.3445 0.9672 7.750 0.8779 0.01627 0.01065 -0.0029 0.3368 0.9738 8.000 0.9058 0.01690 0.01121 -0.0037 0.3288 0.9790 8.250 0.9425 0.01729 0.01162 -0.0061 0.3213 0.9821 8.500 0.9735 0.01789 0.01215 -0.0077 0.3131 0.9863 8.750 1.0039 0.01845 0.01273 -0.0090 0.3056 0.9908 9.000 1.0367 0.01897 0.01321 -0.0111 0.2975 0.9938 9.250 1.0697 0.01950 0.01371 -0.0132 0.2900 0.9972 9.500 1.1023 0.02004 0.01423 -0.0152 0.2820 0.9998 10.000 1.1085 0.02107 0.01525 -0.0084 0.2713 1.0000 10.250 1.1119 0.02168 0.01584 -0.0051 0.2659 1.0000 10.500 1.1135 0.02245 0.01657 -0.0017 0.2603 1.0000 10.750 1.1217 0.02304 0.01718 0.0008 0.2553 1.0000 11.000 1.1281 0.02378 0.01791 0.0033 0.2497 1.0000 11.250 1.1302 0.02478 0.01887 0.0063 0.2442 1.0000 11.500 1.1401 0.02547 0.01959 0.0082 0.2395 1.0000 11.750 1.1467 0.02637 0.02049 0.0104 0.2344 1.0000 12.000 1.1499 0.02750 0.02158 0.0128 0.2292 1.0000 12.250 1.1583 0.02841 0.02253 0.0146 0.2245 1.0000 12.500 1.1655 0.02943 0.02356 0.0164 0.2196 1.0000 12.750 1.1678 0.03081 0.02490 0.0185 0.2147 1.0000 13.000 1.1761 0.03186 0.02598 0.0201 0.2101 1.0000 13.250 1.1825 0.03309 0.02723 0.0216 0.2056 1.0000 13.500 1.1857 0.03456 0.02868 0.0233 0.2011 1.0000 13.750 1.1911 0.03595 0.03009 0.0247 0.1968 1.0000 14.000 1.1985 0.03723 0.03141 0.0259 0.1925 1.0000 14.250 1.2004 0.03896 0.03312 0.0273 0.1883 1.0000 14.500 1.2041 0.04059 0.03476 0.0285 0.1843 1.0000 14.750 1.2103 0.04208 0.03630 0.0294 0.1804 1.0000 15.000 1.2133 0.04386 0.03808 0.0305 0.1765 1.0000 15.250 1.2121 0.04599 0.04019 0.0316 0.1725 1.0000 15.500 1.2196 0.04751 0.04177 0.0323 0.1692 1.0000 15.750 1.2219 0.04948 0.04377 0.0330 0.1651 1.0000 16.000 1.2210 0.05175 0.04603 0.0338 0.1615 1.0000 16.250 1.2246 0.05366 0.04798 0.0344 0.1582 1.0000 16.500 1.2273 0.05574 0.05010 0.0349 0.1544 1.0000 16.750 1.2263 0.05814 0.05250 0.0353 0.1509 1.0000 17.000 1.2257 0.06055 0.05492 0.0358 0.1477 1.0000 17.250 1.2291 0.06266 0.05709 0.0360 0.1441 1.0000 17.500 1.2268 0.06534 0.05978 0.0362 0.1405 1.0000 17.750 1.2245 0.06798 0.06240 0.0364 0.1374 1.0000 18.000 1.2268 0.07033 0.06484 0.0364 0.1340 1.0000 18.250 1.2262 0.07294 0.06747 0.0364 0.1310 1.0000 18.500 1.2232 0.07580 0.07032 0.0363 0.1284 1.0000 18.750 1.2239 0.07831 0.07288 0.0362 0.1258 1.0000 19.000 1.2251 0.08082 0.07544 0.0361 0.1231 1.0000 19.250 1.2232 0.08368 0.07833 0.0358 0.1207 1.0000