XFOIL Version 6.96 Calculated polar for: EPPLER 338 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.2737 0.09332 0.09035 -0.0460 0.6446 0.0061 -9.750 -0.2728 0.08968 0.08668 -0.0475 0.6334 0.0061 -9.250 -0.2771 0.08123 0.07819 -0.0515 0.6134 0.0060 -8.750 -0.2290 0.06337 0.06040 -0.0484 0.5696 0.0055 -8.500 -0.2363 0.05886 0.05590 -0.0510 0.5641 0.0054 -8.250 -0.2534 0.05364 0.05067 -0.0553 0.5602 0.0053 -7.750 -0.2898 0.04608 0.04302 -0.0544 0.5511 0.0051 -6.750 -0.4224 0.01959 0.01412 -0.0339 0.5572 0.0036 -6.500 -0.4041 0.01742 0.01155 -0.0321 0.5487 0.0036 -6.250 -0.3816 0.01629 0.01017 -0.0310 0.5398 0.0037 -6.000 -0.3579 0.01544 0.00914 -0.0302 0.5317 0.0037 -5.750 -0.3340 0.01468 0.00820 -0.0294 0.5227 0.0037 -5.500 -0.3113 0.01354 0.00685 -0.0284 0.5144 0.0041 -5.250 -0.2864 0.01313 0.00634 -0.0277 0.5056 0.0042 -5.000 -0.2607 0.01287 0.00603 -0.0273 0.4975 0.0044 -4.750 -0.2353 0.01256 0.00564 -0.0268 0.4904 0.0046 -4.500 -0.2100 0.01222 0.00523 -0.0262 0.4836 0.0047 -4.250 -0.1848 0.01190 0.00484 -0.0256 0.4764 0.0049 -4.000 -0.1597 0.01156 0.00443 -0.0250 0.4698 0.0051 -3.750 -0.1342 0.01134 0.00414 -0.0244 0.4624 0.0053 -3.500 -0.1087 0.01110 0.00385 -0.0239 0.4562 0.0054 -3.250 -0.0831 0.01088 0.00357 -0.0233 0.4499 0.0056 -2.750 -0.0323 0.01043 0.00304 -0.0222 0.4389 0.0060 -2.500 -0.0065 0.01027 0.00284 -0.0217 0.4328 0.0062 -2.250 0.0194 0.01014 0.00268 -0.0213 0.4270 0.0067 -2.000 0.0456 0.01002 0.00253 -0.0209 0.4218 0.0074 -1.750 0.0717 0.00990 0.00237 -0.0205 0.4167 0.0081 -1.500 0.0977 0.00979 0.00224 -0.0200 0.4119 0.0096 -1.250 0.1241 0.00967 0.00211 -0.0197 0.4078 0.0118 -1.000 0.1504 0.00958 0.00202 -0.0193 0.4030 0.0156 -0.750 0.1765 0.00950 0.00194 -0.0189 0.3979 0.0249 -0.500 0.2024 0.00936 0.00188 -0.0185 0.3940 0.0482 -0.250 0.2278 0.00919 0.00184 -0.0181 0.3903 0.0912 0.000 0.2522 0.00894 0.00179 -0.0175 0.3863 0.1686 0.250 0.2406 0.00662 0.00170 -0.0099 0.3838 0.8350 0.500 0.2651 0.00678 0.00190 -0.0089 0.3798 0.8791 0.750 0.2913 0.00692 0.00200 -0.0083 0.3764 0.8922 1.000 0.3176 0.00705 0.00211 -0.0078 0.3729 0.9003 1.250 0.3435 0.00718 0.00220 -0.0072 0.3693 0.9070 1.500 0.3688 0.00736 0.00235 -0.0064 0.3655 0.9134 1.750 0.3961 0.00743 0.00238 -0.0062 0.3627 0.9160 2.000 0.4242 0.00747 0.00239 -0.0063 0.3594 0.9168 2.250 0.4522 0.00752 0.00240 -0.0064 0.3560 0.9175 2.500 0.4799 0.00759 0.00242 -0.0065 0.3525 0.9183 2.750 0.5077 0.00766 0.00245 -0.0065 0.3491 0.9191 3.000 0.5358 0.00771 0.00248 -0.0067 0.3465 0.9196 3.250 0.5637 0.00776 0.00251 -0.0068 0.3434 0.9202 3.500 0.5912 0.00782 0.00255 -0.0068 0.3398 0.9209 3.750 0.6185 0.00791 0.00261 -0.0068 0.3364 0.9215 4.000 0.6460 0.00797 0.00266 -0.0069 0.3335 0.9221 4.250 0.6736 0.00804 0.00272 -0.0069 0.3305 0.9227 4.500 0.7011 0.00811 0.00280 -0.0070 0.3273 0.9234 4.750 0.7281 0.00821 0.00287 -0.0070 0.3236 0.9242 5.000 0.7548 0.00832 0.00297 -0.0069 0.3198 0.9250 5.250 0.7823 0.00839 0.00305 -0.0070 0.3169 0.9257 5.500 0.8095 0.00847 0.00314 -0.0070 0.3130 0.9264 5.750 0.8363 0.00858 0.00324 -0.0070 0.3092 0.9271 6.000 0.8628 0.00871 0.00335 -0.0069 0.3045 0.9279 6.250 0.8898 0.00880 0.00345 -0.0070 0.2994 0.9287 6.500 0.9157 0.00896 0.00358 -0.0069 0.2919 0.9295 6.750 0.9422 0.00908 0.00370 -0.0068 0.2857 0.9303 7.000 0.9679 0.00925 0.00384 -0.0067 0.2781 0.9311 7.250 0.9940 0.00938 0.00399 -0.0066 0.2728 0.9319 7.500 1.0199 0.00953 0.00414 -0.0065 0.2672 0.9327 7.750 1.0452 0.00972 0.00431 -0.0064 0.2618 0.9335 8.000 1.0705 0.00989 0.00449 -0.0062 0.2542 0.9344 8.250 1.0946 0.01012 0.00469 -0.0058 0.2452 0.9354 8.500 1.1182 0.01034 0.00491 -0.0054 0.2364 0.9365 8.750 1.1416 0.01058 0.00514 -0.0049 0.2274 0.9375 9.000 1.1640 0.01086 0.00540 -0.0042 0.2181 0.9387 9.500 1.2073 0.01147 0.00598 -0.0027 0.1978 0.9412 9.750 1.2279 0.01181 0.00630 -0.0019 0.1881 0.9426 10.000 1.2476 0.01218 0.00666 -0.0008 0.1784 0.9442 10.250 1.2662 0.01258 0.00704 0.0004 0.1678 0.9460 10.500 1.2843 0.01299 0.00743 0.0016 0.1577 0.9478 10.750 1.2995 0.01346 0.00787 0.0033 0.1464 0.9498 11.000 1.3100 0.01393 0.00833 0.0060 0.1355 0.9528 11.250 1.3203 0.01442 0.00882 0.0086 0.1268 0.9565 11.500 1.3307 0.01495 0.00934 0.0111 0.1182 0.9611 11.750 1.3368 0.01572 0.01007 0.0140 0.1054 0.9672 12.250 1.3607 0.01765 0.01196 0.0161 0.0821 0.9820 12.500 1.3784 0.01875 0.01306 0.0155 0.0721 0.9914 12.750 1.3754 0.02048 0.01473 0.0177 0.0577 1.0000 13.000 1.3756 0.02211 0.01636 0.0194 0.0514 1.0000 13.250 1.3787 0.02371 0.01799 0.0205 0.0482 1.0000 13.500 1.3811 0.02551 0.01985 0.0213 0.0458 1.0000 13.750 1.3815 0.02763 0.02201 0.0219 0.0419 1.0000 14.000 1.3841 0.02967 0.02412 0.0223 0.0404 1.0000 14.250 1.3771 0.03269 0.02717 0.0226 0.0361 1.0000 14.500 1.3775 0.03512 0.02966 0.0226 0.0339 1.0000 14.750 1.3815 0.03723 0.03187 0.0226 0.0355 1.0000 15.000 1.3823 0.03970 0.03442 0.0225 0.0354 1.0000 15.250 1.3779 0.04272 0.03752 0.0223 0.0329 1.0000 15.500 1.3657 0.04664 0.04146 0.0220 0.0292 1.0000 15.750 1.3634 0.04957 0.04448 0.0216 0.0294 1.0000 16.000 1.3496 0.05390 0.04882 0.0209 0.0243 1.0000 16.250 1.3462 0.05714 0.05214 0.0203 0.0242 1.0000 16.750 1.3269 0.06534 0.06045 0.0184 0.0189 1.0000 17.000 1.3169 0.06963 0.06478 0.0172 0.0167 1.0000 17.250 1.3106 0.07353 0.06876 0.0161 0.0160 1.0000 17.500 1.3079 0.07704 0.07234 0.0151 0.0160 1.0000 17.750 1.2996 0.08132 0.07669 0.0137 0.0142 1.0000 18.000 1.2904 0.08580 0.08122 0.0122 0.0126 1.0000