XFOIL Version 6.96 Calculated polar for: EPPLER 638 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.2815 0.09906 0.09598 -0.0346 0.6065 0.0046 -10.000 -0.2809 0.09486 0.09176 -0.0362 0.5949 0.0052 -8.500 -0.5590 0.02170 0.01698 -0.0425 0.6021 0.0054 -8.250 -0.5467 0.01870 0.01350 -0.0403 0.5921 0.0056 -8.000 -0.5260 0.01744 0.01201 -0.0392 0.5822 0.0057 -7.750 -0.5029 0.01671 0.01111 -0.0384 0.5719 0.0059 -7.500 -0.4794 0.01600 0.01025 -0.0376 0.5607 0.0061 -7.250 -0.4547 0.01551 0.00965 -0.0369 0.5502 0.0063 -7.000 -0.4300 0.01502 0.00904 -0.0363 0.5406 0.0065 -6.750 -0.4055 0.01441 0.00828 -0.0356 0.5316 0.0067 -6.500 -0.3803 0.01397 0.00772 -0.0350 0.5235 0.0070 -6.250 -0.3553 0.01344 0.00706 -0.0344 0.5149 0.0073 -6.000 -0.3300 0.01300 0.00650 -0.0338 0.5068 0.0075 -5.750 -0.3044 0.01267 0.00607 -0.0333 0.4981 0.0077 -5.500 -0.2786 0.01232 0.00566 -0.0328 0.4903 0.0082 -5.250 -0.2522 0.01216 0.00544 -0.0324 0.4827 0.0086 -5.000 -0.2255 0.01200 0.00524 -0.0320 0.4764 0.0091 -4.750 -0.1994 0.01174 0.00490 -0.0316 0.4695 0.0095 -4.500 -0.1734 0.01147 0.00455 -0.0311 0.4631 0.0100 -4.250 -0.1473 0.01122 0.00422 -0.0306 0.4560 0.0104 -4.000 -0.1212 0.01100 0.00397 -0.0301 0.4497 0.0110 -3.750 -0.0942 0.01090 0.00384 -0.0299 0.4437 0.0115 -3.500 -0.0676 0.01078 0.00367 -0.0295 0.4379 0.0122 -3.250 -0.0406 0.01067 0.00352 -0.0292 0.4329 0.0131 -3.000 -0.0138 0.01056 0.00336 -0.0289 0.4270 0.0136 -2.750 0.0119 0.01034 0.00310 -0.0284 0.4212 0.0144 -2.500 0.0388 0.01023 0.00297 -0.0281 0.4163 0.0151 -2.250 0.0655 0.01010 0.00282 -0.0277 0.4114 0.0159 -1.750 0.1191 0.00993 0.00256 -0.0271 0.4027 0.0175 -1.500 0.1451 0.00973 0.00233 -0.0266 0.3978 0.0183 -1.250 0.1715 0.00962 0.00219 -0.0262 0.3933 0.0193 -1.000 0.1983 0.00953 0.00209 -0.0259 0.3894 0.0203 -0.750 0.2252 0.00945 0.00198 -0.0256 0.3857 0.0211 -0.500 0.2521 0.00938 0.00189 -0.0254 0.3819 0.0219 -0.250 0.2790 0.00935 0.00181 -0.0251 0.3777 0.0225 0.000 0.3058 0.00928 0.00173 -0.0248 0.3740 0.0245 0.250 0.3329 0.00923 0.00168 -0.0246 0.3707 0.0263 0.500 0.3599 0.00921 0.00164 -0.0244 0.3673 0.0286 0.750 0.3863 0.00913 0.00163 -0.0240 0.3639 0.0557 1.000 0.4120 0.00899 0.00163 -0.0236 0.3607 0.1190 1.250 0.4107 0.00700 0.00160 -0.0182 0.3588 0.7840 1.500 0.4371 0.00675 0.00177 -0.0174 0.3556 0.9259 1.750 0.4785 0.00691 0.00192 -0.0202 0.3519 0.9515 2.000 0.5121 0.00707 0.00203 -0.0213 0.3487 0.9626 2.250 0.5407 0.00722 0.00215 -0.0213 0.3458 0.9717 2.500 0.5814 0.00734 0.00224 -0.0241 0.3426 0.9736 2.750 0.6179 0.00745 0.00231 -0.0260 0.3393 0.9753 3.000 0.6490 0.00754 0.00236 -0.0268 0.3364 0.9766 3.250 0.6794 0.00764 0.00243 -0.0275 0.3334 0.9780 3.500 0.7091 0.00772 0.00249 -0.0280 0.3307 0.9797 3.750 0.7374 0.00780 0.00256 -0.0281 0.3281 0.9818 4.000 0.7636 0.00790 0.00264 -0.0279 0.3253 0.9841 4.250 0.7954 0.00798 0.00272 -0.0289 0.3224 0.9847 4.500 0.8268 0.00809 0.00280 -0.0298 0.3193 0.9854 4.750 0.8581 0.00819 0.00290 -0.0307 0.3165 0.9863 5.000 0.8892 0.00827 0.00298 -0.0316 0.3137 0.9872 5.250 0.9198 0.00836 0.00307 -0.0324 0.3108 0.9882 5.500 0.9499 0.00847 0.00318 -0.0331 0.3076 0.9894 5.750 0.9794 0.00861 0.00331 -0.0337 0.3035 0.9907 6.000 1.0088 0.00871 0.00342 -0.0342 0.3000 0.9919 6.250 1.0374 0.00882 0.00354 -0.0346 0.2960 0.9932 6.500 1.0657 0.00897 0.00368 -0.0349 0.2915 0.9943 6.750 1.0963 0.00911 0.00382 -0.0358 0.2874 0.9951 7.000 1.1267 0.00922 0.00395 -0.0367 0.2824 0.9959 7.250 1.1562 0.00940 0.00412 -0.0374 0.2764 0.9968 7.500 1.1860 0.00954 0.00428 -0.0381 0.2717 0.9978 7.750 1.2155 0.00971 0.00445 -0.0389 0.2658 0.9987 8.000 1.2444 0.00992 0.00465 -0.0395 0.2599 0.9995 8.250 1.2713 0.01009 0.00485 -0.0397 0.2532 1.0000 8.500 1.2918 0.01035 0.00508 -0.0385 0.2452 1.0000 8.750 1.3123 0.01060 0.00532 -0.0374 0.2364 1.0000 9.000 1.3327 0.01084 0.00558 -0.0363 0.2298 1.0000 9.250 1.3515 0.01118 0.00588 -0.0349 0.2196 1.0000 9.500 1.3709 0.01147 0.00617 -0.0336 0.2105 1.0000 9.750 1.3884 0.01185 0.00653 -0.0320 0.1988 1.0000 10.000 1.4043 0.01232 0.00695 -0.0302 0.1849 1.0000 10.250 1.4154 0.01301 0.00753 -0.0277 0.1638 1.0000 10.500 1.4246 0.01376 0.00816 -0.0248 0.1430 1.0000 10.750 1.4329 0.01451 0.00882 -0.0219 0.1257 1.0000 11.000 1.4397 0.01527 0.00951 -0.0188 0.1092 1.0000 11.250 1.4478 0.01593 0.01014 -0.0158 0.0989 1.0000 11.500 1.4491 0.01664 0.01081 -0.0117 0.0888 1.0000 11.750 1.4492 0.01740 0.01155 -0.0076 0.0800 1.0000 12.000 1.4524 0.01821 0.01237 -0.0044 0.0722 1.0000 12.250 1.4539 0.01926 0.01341 -0.0014 0.0646 1.0000 12.500 1.4535 0.02062 0.01477 0.0011 0.0572 1.0000 12.750 1.4563 0.02204 0.01622 0.0027 0.0519 1.0000 13.000 1.4530 0.02417 0.01836 0.0040 0.0443 1.0000 13.250 1.4562 0.02606 0.02031 0.0046 0.0417 1.0000 13.500 1.4510 0.02890 0.02317 0.0050 0.0353 1.0000 13.750 1.4484 0.03167 0.02599 0.0050 0.0322 1.0000 14.000 1.4442 0.03469 0.02907 0.0049 0.0286 1.0000 14.250 1.4320 0.03863 0.03305 0.0047 0.0238 1.0000 14.500 1.4309 0.04142 0.03592 0.0045 0.0235 1.0000 14.750 1.4149 0.04588 0.04042 0.0040 0.0193 1.0000 15.000 1.4111 0.04902 0.04365 0.0037 0.0193 1.0000 15.250 1.4001 0.05300 0.04769 0.0032 0.0171 1.0000 15.500 1.3885 0.05719 0.05195 0.0025 0.0155 1.0000 15.750 1.3797 0.06117 0.05600 0.0018 0.0141 1.0000 16.000 1.3740 0.06480 0.05970 0.0011 0.0136 1.0000 16.250 1.3639 0.06905 0.06402 0.0002 0.0122 1.0000 16.500 1.3562 0.07305 0.06809 -0.0007 0.0113 1.0000 16.750 1.3415 0.07802 0.07310 -0.0018 0.0086 1.0000 17.000 1.3397 0.08134 0.07652 -0.0026 0.0091 1.0000 17.250 1.3252 0.08643 0.08165 -0.0039 0.0066 1.0000 17.500 1.3197 0.09031 0.08560 -0.0050 0.0062 1.0000