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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3217 0.09168 0.08841 -0.0305 1.0000 0.0220 -8.750 -0.3230 0.08805 0.08483 -0.0320 1.0000 0.0222 -8.500 -0.3262 0.08428 0.08113 -0.0337 1.0000 0.0223 -8.250 -0.3056 0.07719 0.07397 -0.0456 0.9076 0.0227 -8.000 -0.2887 0.07029 0.06677 -0.0563 0.8386 0.0231 -7.000 -0.3138 0.05105 0.04642 -0.0532 0.7359 0.0132 -6.750 -0.3061 0.04922 0.04444 -0.0518 0.7168 0.0130 -6.500 -0.2994 0.04663 0.04163 -0.0500 0.7011 0.0128 -6.250 -0.2924 0.04352 0.03824 -0.0478 0.6868 0.0126 -6.000 -0.2824 0.04073 0.03518 -0.0458 0.6734 0.0123 -5.750 -0.2714 0.03770 0.03183 -0.0434 0.6605 0.0119 -5.500 -0.2596 0.03429 0.02804 -0.0408 0.6496 0.0118 -5.250 -0.2454 0.03118 0.02451 -0.0382 0.6388 0.0116 -5.000 -0.2289 0.02825 0.02114 -0.0359 0.6281 0.0117 -4.750 -0.2098 0.02578 0.01821 -0.0338 0.6179 0.0120 -4.500 -0.1879 0.02359 0.01545 -0.0321 0.6073 0.0130 -4.250 -0.1647 0.02221 0.01378 -0.0310 0.5965 0.0137 -4.000 -0.1405 0.02126 0.01264 -0.0302 0.5864 0.0143 -3.750 -0.1146 0.02002 0.01112 -0.0295 0.5764 0.0145 -3.500 -0.0883 0.01894 0.00982 -0.0288 0.5675 0.0148 -3.250 -0.0623 0.01802 0.00873 -0.0282 0.5583 0.0152 -3.000 -0.0368 0.01723 0.00780 -0.0274 0.5494 0.0158 -2.750 -0.0125 0.01658 0.00700 -0.0265 0.5409 0.0165 -2.500 0.0111 0.01603 0.00642 -0.0256 0.5326 0.0172 -2.250 0.0345 0.01561 0.00593 -0.0247 0.5251 0.0187 -2.000 0.0582 0.01524 0.00552 -0.0238 0.5179 0.0218 -1.750 0.0818 0.01493 0.00514 -0.0229 0.5106 0.0262 -1.500 0.1053 0.01461 0.00478 -0.0219 0.5038 0.0332 -1.250 0.1284 0.01428 0.00448 -0.0209 0.4966 0.0528 -1.000 0.1498 0.01386 0.00426 -0.0197 0.4908 0.1174 -0.500 0.2002 0.01295 0.00594 -0.0156 0.4786 0.9103 -0.250 0.2608 0.01367 0.00643 -0.0211 0.4709 0.9350 0.000 0.3303 0.01408 0.00660 -0.0289 0.4627 0.9500 0.250 0.3656 0.01409 0.00646 -0.0306 0.4575 0.9522 0.500 0.3959 0.01409 0.00636 -0.0312 0.4519 0.9542 0.750 0.4241 0.01411 0.00627 -0.0314 0.4467 0.9566 1.000 0.4501 0.01416 0.00621 -0.0312 0.4421 0.9592 1.250 0.4724 0.01420 0.00621 -0.0302 0.4369 0.9622 1.500 0.5014 0.01422 0.00615 -0.0306 0.4324 0.9637 1.750 0.5309 0.01427 0.00609 -0.0311 0.4282 0.9651 2.000 0.5601 0.01430 0.00609 -0.0316 0.4234 0.9666 2.250 0.5879 0.01434 0.00610 -0.0318 0.4188 0.9683 2.500 0.6144 0.01441 0.00610 -0.0317 0.4147 0.9700 2.750 0.6399 0.01451 0.00614 -0.0315 0.4112 0.9719 3.000 0.6637 0.01458 0.00623 -0.0308 0.4068 0.9737 3.250 0.6896 0.01466 0.00629 -0.0306 0.4026 0.9753 3.500 0.7182 0.01474 0.00633 -0.0311 0.3988 0.9764 3.750 0.7454 0.01485 0.00640 -0.0312 0.3953 0.9774 4.000 0.7726 0.01493 0.00653 -0.0313 0.3910 0.9786 4.250 0.7996 0.01503 0.00664 -0.0315 0.3869 0.9801 4.500 0.8253 0.01516 0.00675 -0.0313 0.3834 0.9814 4.750 0.8498 0.01531 0.00687 -0.0309 0.3801 0.9826 5.000 0.8743 0.01544 0.00708 -0.0305 0.3759 0.9841 5.250 0.8988 0.01558 0.00726 -0.0301 0.3719 0.9856 5.500 0.9257 0.01572 0.00739 -0.0303 0.3681 0.9864 5.750 0.9518 0.01589 0.00757 -0.0303 0.3647 0.9873 6.000 0.9777 0.01603 0.00781 -0.0302 0.3604 0.9883 6.250 1.0032 0.01619 0.00802 -0.0301 0.3560 0.9894 6.500 1.0291 0.01636 0.00821 -0.0301 0.3520 0.9908 6.750 1.0542 0.01656 0.00846 -0.0300 0.3481 0.9921 7.000 1.0781 0.01675 0.00875 -0.0296 0.3433 0.9932 7.250 1.1015 0.01694 0.00901 -0.0291 0.3389 0.9944 7.500 1.1262 0.01717 0.00923 -0.0289 0.3350 0.9953 7.750 1.1509 0.01736 0.00957 -0.0288 0.3295 0.9965 8.000 1.1751 0.01756 0.00985 -0.0286 0.3239 0.9977 8.250 1.1998 0.01779 0.01012 -0.0285 0.3180 0.9992 8.500 1.2209 0.01801 0.01047 -0.0276 0.3112 1.0000 8.750 1.2364 0.01826 0.01074 -0.0257 0.3058 1.0000 9.000 1.2516 0.01851 0.01112 -0.0237 0.2990 1.0000 9.250 1.2650 0.01878 0.01144 -0.0213 0.2926 1.0000 9.500 1.2780 0.01907 0.01182 -0.0190 0.2863 1.0000 9.750 1.2894 0.01936 0.01221 -0.0164 0.2801 1.0000 10.000 1.2992 0.01969 0.01259 -0.0134 0.2749 1.0000 10.250 1.3078 0.02000 0.01302 -0.0104 0.2686 1.0000 10.500 1.3121 0.02035 0.01339 -0.0065 0.2627 1.0000 10.750 1.3159 0.02069 0.01383 -0.0026 0.2558 1.0000 11.000 1.3122 0.02103 0.01421 0.0026 0.2494 1.0000 11.250 1.3107 0.02141 0.01466 0.0072 0.2427 1.0000 11.500 1.3108 0.02198 0.01524 0.0111 0.2350 1.0000 11.750 1.3158 0.02265 0.01599 0.0139 0.2262 1.0000 12.000 1.3196 0.02351 0.01689 0.0164 0.2186 1.0000 12.250 1.3235 0.02452 0.01797 0.0185 0.2100 1.0000 12.500 1.3261 0.02575 0.01926 0.0203 0.2017 1.0000 12.750 1.3252 0.02734 0.02088 0.0220 0.1931 1.0000 13.000 1.3268 0.02899 0.02261 0.0232 0.1846 1.0000 13.250 1.3242 0.03110 0.02476 0.0241 0.1759 1.0000 13.500 1.3208 0.03345 0.02717 0.0248 0.1682 1.0000 13.750 1.3174 0.03596 0.02975 0.0252 0.1604 1.0000 14.000 1.3097 0.03899 0.03281 0.0254 0.1534 1.0000 14.250 1.3046 0.04192 0.03583 0.0253 0.1458 1.0000 14.500 1.2947 0.04542 0.03937 0.0251 0.1387 1.0000 14.750 1.2861 0.04891 0.04292 0.0247 0.1316 1.0000 15.000 1.2757 0.05270 0.04677 0.0241 0.1247 1.0000 15.250 1.2641 0.05677 0.05088 0.0233 0.1178 1.0000 15.500 1.2546 0.06075 0.05493 0.0224 0.1113 1.0000 15.750 1.2433 0.06506 0.05928 0.0213 0.1053 1.0000 16.000 1.2342 0.06923 0.06351 0.0201 0.0992 1.0000 16.250 1.2240 0.07365 0.06797 0.0188 0.0938 1.0000 16.500 1.2155 0.07795 0.07233 0.0174 0.0879 1.0000 16.750 1.2061 0.08245 0.07688 0.0159 0.0828 1.0000 17.000 1.1991 0.08671 0.08120 0.0144 0.0779 1.0000 17.250 1.1908 0.09127 0.08582 0.0127 0.0729 1.0000