XFOIL Version 6.96 Calculated polar for: E423 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 ------ -------- --------- --------- -------- -------- -------- -10.000 0.3483 0.08971 0.08619 -0.1735 0.8041 0.0196 -9.750 0.3588 0.08785 0.08423 -0.1733 0.7873 0.0197 -9.500 0.3680 0.08620 0.08249 -0.1731 0.7726 0.0201 -9.250 0.3761 0.08448 0.08068 -0.1732 0.7603 0.0202 -9.000 0.3840 0.08276 0.07891 -0.1732 0.7493 0.0206 -8.750 0.3918 0.08095 0.07704 -0.1733 0.7400 0.0210 -8.500 0.3993 0.07913 0.07519 -0.1734 0.7314 0.0214 -8.250 0.4061 0.07714 0.07314 -0.1738 0.7240 0.0222 -8.000 0.4082 0.07503 0.07104 -0.1746 0.7169 0.0227 -7.750 0.4088 0.07304 0.06903 -0.1753 0.7100 0.0228 -7.500 0.4179 0.07087 0.06683 -0.1749 0.7041 0.0230 -7.250 0.4298 0.06927 0.06523 -0.1742 0.6981 0.0233 -7.000 0.4378 0.06772 0.06365 -0.1739 0.6924 0.0235 -6.750 0.4461 0.06618 0.06206 -0.1737 0.6872 0.0239 -6.500 0.4514 0.06458 0.06051 -0.1731 0.6825 0.0247 -6.250 0.4544 0.06296 0.05890 -0.1723 0.6776 0.0253 -6.000 0.4471 0.06080 0.05674 -0.1726 0.6729 0.0263 -5.750 0.4518 0.02067 0.01569 -0.2281 0.6709 0.0153 -5.500 0.4894 0.01736 0.01179 -0.2336 0.6668 0.0158 -5.250 0.5198 0.01608 0.01018 -0.2352 0.6627 0.0163 -5.000 0.5489 0.01508 0.00904 -0.2362 0.6585 0.0172 -4.750 0.5782 0.01455 0.00835 -0.2368 0.6548 0.0179 -4.500 0.6091 0.01408 0.00766 -0.2377 0.6509 0.0190 -4.250 0.6371 0.01351 0.00702 -0.2380 0.6477 0.0202 -4.000 0.6652 0.01318 0.00662 -0.2381 0.6440 0.0220 -3.750 0.6935 0.01286 0.00622 -0.2384 0.6404 0.0246 -3.500 0.7224 0.01263 0.00590 -0.2386 0.6370 0.0287 -3.250 0.7528 0.01248 0.00562 -0.2392 0.6336 0.0351 -3.000 0.7807 0.01224 0.00538 -0.2393 0.6307 0.0417 -2.750 0.8078 0.01212 0.00525 -0.2392 0.6274 0.0483 -2.500 0.8352 0.01203 0.00514 -0.2391 0.6241 0.0552 -2.250 0.8631 0.01196 0.00503 -0.2391 0.6211 0.0620 -2.000 0.8917 0.01193 0.00495 -0.2392 0.6181 0.0698 -1.750 0.9219 0.01198 0.00494 -0.2398 0.6148 0.0787 -1.500 0.9479 0.01195 0.00491 -0.2393 0.6121 0.0869 -1.250 0.9746 0.01190 0.00489 -0.2391 0.6091 0.0966 -1.000 1.0017 0.01188 0.00488 -0.2389 0.6062 0.1060 -0.750 1.0290 0.01189 0.00486 -0.2388 0.6033 0.1151 -0.500 1.0568 0.01197 0.00491 -0.2388 0.6004 0.1241 -0.250 1.0871 0.01209 0.00498 -0.2394 0.5971 0.1336 0.000 1.1123 0.01214 0.00504 -0.2388 0.5946 0.1418 0.250 1.1382 0.01214 0.00508 -0.2384 0.5919 0.1514 0.500 1.1643 0.01221 0.00514 -0.2381 0.5889 0.1595 0.750 1.1907 0.01222 0.00516 -0.2378 0.5860 0.1689 1.000 1.2176 0.01232 0.00521 -0.2377 0.5832 0.1771 1.250 1.2470 0.01242 0.00530 -0.2381 0.5803 0.1869 1.500 1.2732 0.01253 0.00541 -0.2378 0.5776 0.1955 1.750 1.2977 0.01254 0.00548 -0.2372 0.5748 0.2049 2.000 1.3227 0.01261 0.00556 -0.2367 0.5718 0.2140 2.250 1.3483 0.01265 0.00564 -0.2363 0.5689 0.2247 2.500 1.3743 0.01273 0.00572 -0.2360 0.5661 0.2360 2.750 1.4024 0.01287 0.00584 -0.2362 0.5631 0.2491 3.000 1.4288 0.01299 0.00601 -0.2361 0.5602 0.2647 3.250 1.4517 0.01304 0.00615 -0.2352 0.5574 0.2820 3.500 1.4754 0.01310 0.00628 -0.2345 0.5543 0.3058 3.750 1.4997 0.01314 0.00643 -0.2339 0.5512 0.3432 4.000 1.5251 0.01314 0.00661 -0.2337 0.5482 0.4374 4.250 1.5496 0.01268 0.00686 -0.2333 0.5452 1.0000 4.500 1.5725 0.01285 0.00703 -0.2324 0.5421 1.0000 4.750 1.5925 0.01297 0.00718 -0.2309 0.5389 1.0000 5.000 1.6130 0.01310 0.00731 -0.2296 0.5354 1.0000 5.250 1.6339 0.01324 0.00743 -0.2283 0.5319 1.0000 5.500 1.6587 0.01344 0.00757 -0.2279 0.5282 1.0000 5.750 1.6786 0.01363 0.00779 -0.2265 0.5247 1.0000 6.000 1.6956 0.01378 0.00798 -0.2245 0.5208 1.0000 6.250 1.7141 0.01394 0.00815 -0.2228 0.5169 1.0000 6.500 1.7344 0.01413 0.00832 -0.2215 0.5130 1.0000 6.750 1.7566 0.01438 0.00855 -0.2207 0.5090 1.0000 7.000 1.7723 0.01458 0.00882 -0.2185 0.5051 1.0000 7.250 1.7889 0.01479 0.00907 -0.2166 0.5006 1.0000 7.500 1.8074 0.01503 0.00929 -0.2150 0.4964 1.0000 7.750 1.8266 0.01532 0.00959 -0.2137 0.4920 1.0000 8.000 1.8411 0.01559 0.00994 -0.2114 0.4873 1.0000 8.250 1.8568 0.01589 0.01026 -0.2095 0.4824 1.0000 8.500 1.8743 0.01625 0.01058 -0.2079 0.4776 1.0000 8.750 1.8885 0.01661 0.01102 -0.2057 0.4727 1.0000 9.000 1.9027 0.01699 0.01146 -0.2036 0.4671 1.0000 9.250 1.9167 0.01745 0.01189 -0.2015 0.4618 1.0000 9.500 1.9301 0.01792 0.01244 -0.1994 0.4562 1.0000 9.750 1.9426 0.01844 0.01300 -0.1971 0.4501 1.0000 10.000 1.9537 0.01908 0.01361 -0.1947 0.4440 1.0000 10.250 1.9655 0.01967 0.01431 -0.1925 0.4376 1.0000 10.500 1.9751 0.02042 0.01506 -0.1901 0.4308 1.0000 10.750 1.9848 0.02120 0.01589 -0.1877 0.4242 1.0000 11.000 1.9930 0.02209 0.01682 -0.1852 0.4167 1.0000 11.250 1.9999 0.02311 0.01786 -0.1826 0.4093 1.0000 11.500 2.0065 0.02419 0.01899 -0.1801 0.4010 1.0000 11.750 2.0108 0.02548 0.02029 -0.1775 0.3931 1.0000 12.000 2.0146 0.02688 0.02173 -0.1749 0.3839 1.0000 12.250 2.0177 0.02840 0.02328 -0.1724 0.3754 1.0000 12.500 2.0177 0.03024 0.02513 -0.1697 0.3657 1.0000 12.750 2.0190 0.03207 0.02700 -0.1673 0.3555 1.0000 13.000 2.0159 0.03434 0.02927 -0.1647 0.3454 1.0000 13.250 2.0128 0.03673 0.03168 -0.1623 0.3345 1.0000 13.500 2.0095 0.03926 0.03423 -0.1601 0.3233 1.0000 13.750 2.0030 0.04216 0.03714 -0.1578 0.3124 1.0000 14.000 1.9938 0.04547 0.04044 -0.1555 0.3009 1.0000 14.250 1.9887 0.04850 0.04349 -0.1538 0.2893 1.0000 14.500 1.9812 0.05185 0.04686 -0.1520 0.2783 1.0000 14.750 1.9712 0.05558 0.05058 -0.1503 0.2676 1.0000 15.000 1.9631 0.05922 0.05423 -0.1488 0.2565 1.0000 15.250 1.9564 0.06280 0.05783 -0.1476 0.2464 1.0000 15.500 1.9467 0.06680 0.06183 -0.1464 0.2366 1.0000 15.750 1.9403 0.07049 0.06554 -0.1455 0.2268 1.0000 16.000 1.9349 0.07413 0.06921 -0.1447 0.2178 1.0000 16.250 1.9250 0.07840 0.07347 -0.1439 0.2089 1.0000 16.500 1.9225 0.08177 0.07689 -0.1434 0.2002 1.0000 16.750 1.9145 0.08591 0.08103 -0.1429 0.1922 1.0000 17.000 1.9107 0.08956 0.08472 -0.1426 0.1840 1.0000