XFOIL Version 6.96 Calculated polar for: EPPLER 334 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.2222 0.08511 0.08218 -0.0517 0.7821 0.0089 -8.500 -0.2220 0.08202 0.07898 -0.0526 0.7546 0.0092 -8.250 -0.2218 0.07892 0.07581 -0.0537 0.7313 0.0092 -8.000 -0.2235 0.07558 0.07240 -0.0552 0.7109 0.0094 -7.750 -0.2276 0.07228 0.06906 -0.0571 0.6936 0.0092 -7.500 -0.2361 0.06895 0.06568 -0.0583 0.6797 0.0093 -7.250 -0.2386 0.06597 0.06263 -0.0589 0.6666 0.0092 -7.000 -0.2399 0.06146 0.05801 -0.0606 0.6561 0.0097 -6.750 -0.2354 0.05812 0.05457 -0.0609 0.6444 0.0097 -6.250 -0.2211 0.05020 0.04632 -0.0608 0.6239 0.0099 -6.000 -0.2158 0.04603 0.04198 -0.0598 0.6144 0.0074 -5.750 -0.2040 0.04350 0.03930 -0.0591 0.6040 0.0071 -5.500 -0.1913 0.04040 0.03601 -0.0580 0.5945 0.0069 -5.250 -0.1774 0.03698 0.03236 -0.0566 0.5863 0.0067 -5.000 -0.1621 0.03369 0.02880 -0.0549 0.5777 0.0065 -4.750 -0.1459 0.03010 0.02490 -0.0529 0.5699 0.0066 -4.500 -0.1288 0.02622 0.02064 -0.0506 0.5620 0.0070 -4.250 -0.1099 0.02266 0.01667 -0.0483 0.5544 0.0070 -4.000 -0.0889 0.01904 0.01241 -0.0459 0.5462 0.0076 -3.750 -0.0657 0.01798 0.01119 -0.0453 0.5377 0.0080 -3.500 -0.0411 0.01684 0.00980 -0.0445 0.5296 0.0081 -3.250 -0.0156 0.01523 0.00784 -0.0434 0.5222 0.0079 -3.000 0.0100 0.01431 0.00670 -0.0427 0.5139 0.0078 -2.750 0.0357 0.01360 0.00585 -0.0421 0.5061 0.0078 -2.500 0.0610 0.01305 0.00518 -0.0414 0.4982 0.0078 -2.250 0.0863 0.01254 0.00458 -0.0408 0.4914 0.0079 -2.000 0.1115 0.01212 0.00410 -0.0402 0.4844 0.0081 -1.750 0.1367 0.01178 0.00369 -0.0395 0.4778 0.0083 -1.500 0.1623 0.01151 0.00337 -0.0390 0.4709 0.0085 -1.250 0.1877 0.01128 0.00307 -0.0384 0.4642 0.0090 -1.000 0.2139 0.01108 0.00282 -0.0380 0.4583 0.0096 -0.750 0.2398 0.01090 0.00259 -0.0375 0.4523 0.0109 -0.500 0.2660 0.01078 0.00242 -0.0370 0.4467 0.0132 -0.250 0.2920 0.01062 0.00229 -0.0366 0.4406 0.0258 0.000 0.3171 0.01040 0.00223 -0.0361 0.4350 0.0816 0.250 0.3309 0.00898 0.00213 -0.0342 0.4310 0.5228 0.500 0.3341 0.00814 0.00252 -0.0280 0.4270 0.9003 0.750 0.3551 0.00833 0.00268 -0.0259 0.4220 0.9257 1.000 0.3781 0.00848 0.00275 -0.0245 0.4170 0.9375 1.250 0.4023 0.00863 0.00286 -0.0233 0.4125 0.9507 1.500 0.4379 0.00883 0.00299 -0.0245 0.4072 0.9599 1.750 0.4622 0.00890 0.00297 -0.0238 0.4027 0.9625 2.000 0.4884 0.00894 0.00296 -0.0235 0.3985 0.9639 2.250 0.5180 0.00900 0.00297 -0.0239 0.3938 0.9648 2.500 0.5471 0.00908 0.00299 -0.0243 0.3893 0.9657 2.750 0.5755 0.00916 0.00302 -0.0245 0.3851 0.9667 3.000 0.6041 0.00922 0.00306 -0.0248 0.3809 0.9677 3.250 0.6322 0.00930 0.00311 -0.0250 0.3766 0.9688 3.500 0.6597 0.00941 0.00317 -0.0250 0.3722 0.9702 3.750 0.6873 0.00949 0.00323 -0.0251 0.3686 0.9718 4.000 0.7139 0.00956 0.00330 -0.0250 0.3644 0.9736 4.250 0.7386 0.00965 0.00338 -0.0245 0.3604 0.9755 4.500 0.7675 0.00979 0.00348 -0.0249 0.3562 0.9763 4.750 0.7973 0.00988 0.00358 -0.0255 0.3522 0.9771 5.000 0.8268 0.00998 0.00369 -0.0261 0.3477 0.9780 5.250 0.8556 0.01012 0.00382 -0.0266 0.3432 0.9790 5.500 0.8844 0.01025 0.00395 -0.0270 0.3389 0.9801 5.750 0.9132 0.01036 0.00408 -0.0274 0.3342 0.9813 6.000 0.9414 0.01051 0.00424 -0.0278 0.3291 0.9829 6.250 0.9688 0.01067 0.00440 -0.0280 0.3246 0.9846 6.500 0.9971 0.01079 0.00455 -0.0284 0.3196 0.9860 6.750 1.0268 0.01097 0.00474 -0.0291 0.3137 0.9867 7.000 1.0563 0.01114 0.00493 -0.0298 0.3083 0.9876 7.250 1.0857 0.01131 0.00513 -0.0305 0.3019 0.9886 7.500 1.1141 0.01153 0.00536 -0.0311 0.2960 0.9899 7.750 1.1428 0.01170 0.00557 -0.0316 0.2888 0.9913 8.000 1.1702 0.01195 0.00582 -0.0320 0.2804 0.9930 8.250 1.1975 0.01218 0.00608 -0.0324 0.2717 0.9948 8.500 1.2249 0.01245 0.00637 -0.0328 0.2632 0.9972 8.750 1.2515 0.01278 0.00669 -0.0331 0.2528 0.9997 9.000 1.2678 0.01302 0.00697 -0.0312 0.2444 1.0000 9.250 1.2820 0.01331 0.00726 -0.0289 0.2363 1.0000 9.500 1.2966 0.01367 0.00761 -0.0268 0.2257 1.0000 9.750 1.3136 0.01404 0.00798 -0.0252 0.2147 1.0000 10.000 1.3301 0.01449 0.00841 -0.0236 0.2024 1.0000 10.250 1.3460 0.01499 0.00890 -0.0220 0.1897 1.0000 10.500 1.3606 0.01555 0.00944 -0.0203 0.1763 1.0000 10.750 1.3734 0.01618 0.01003 -0.0182 0.1628 1.0000 11.000 1.3825 0.01685 0.01067 -0.0156 0.1498 1.0000 11.250 1.3913 0.01754 0.01135 -0.0130 0.1387 1.0000 11.500 1.3996 0.01830 0.01210 -0.0105 0.1291 1.0000 11.750 1.4056 0.01920 0.01300 -0.0079 0.1188 1.0000 12.000 1.4114 0.02017 0.01398 -0.0056 0.1091 1.0000 12.250 1.4164 0.02126 0.01509 -0.0034 0.1007 1.0000 12.500 1.4188 0.02262 0.01646 -0.0014 0.0925 1.0000 13.000 1.4216 0.02594 0.01985 0.0017 0.0780 1.0000 13.250 1.4211 0.02802 0.02195 0.0027 0.0724 1.0000 13.500 1.4218 0.03016 0.02415 0.0033 0.0673 1.0000 13.750 1.4191 0.03276 0.02681 0.0038 0.0623 1.0000 14.000 1.4183 0.03529 0.02942 0.0040 0.0583 1.0000 14.250 1.4123 0.03846 0.03263 0.0041 0.0538 1.0000 14.500 1.4089 0.04145 0.03570 0.0039 0.0502 1.0000 14.750 1.3994 0.04518 0.03946 0.0036 0.0458 1.0000 15.000 1.3951 0.04841 0.04278 0.0033 0.0433 1.0000 15.250 1.3881 0.05201 0.04646 0.0028 0.0406 1.0000 15.500 1.3787 0.05600 0.05051 0.0020 0.0377 1.0000 15.750 1.3724 0.05973 0.05432 0.0013 0.0354 1.0000 16.000 1.3647 0.06376 0.05843 0.0003 0.0334 1.0000 16.250 1.3562 0.06797 0.06271 -0.0008 0.0311 1.0000 16.500 1.3501 0.07197 0.06679 -0.0019 0.0294 1.0000 16.750 1.3422 0.07629 0.07119 -0.0033 0.0275 1.0000 17.000 1.3346 0.08065 0.07562 -0.0047 0.0257 1.0000 17.250 1.3291 0.08478 0.07984 -0.0060 0.0244 1.0000 17.500 1.3221 0.08923 0.08437 -0.0076 0.0229 1.0000 18.000 1.3072 0.09845 0.09372 -0.0111 0.0194 1.0000 18.250 1.3018 0.10282 0.09818 -0.0128 0.0186 1.0000