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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.2748 0.07913 0.07569 -0.0424 0.6353 0.0075 -8.500 -0.2770 0.07560 0.07215 -0.0442 0.6243 0.0075 -8.250 -0.2864 0.07141 0.06796 -0.0470 0.6160 0.0075 -8.000 -0.2938 0.06832 0.06483 -0.0477 0.6062 0.0074 -7.750 -0.2982 0.06478 0.06124 -0.0487 0.5984 0.0073 -7.500 -0.2981 0.06118 0.05756 -0.0495 0.5892 0.0072 -7.250 -0.2990 0.05662 0.05289 -0.0502 0.5817 0.0072 -7.000 -0.3000 0.05121 0.04730 -0.0502 0.5752 0.0074 -6.750 -0.2915 0.04791 0.04386 -0.0498 0.5670 0.0072 -6.500 -0.2961 0.03961 0.03517 -0.0475 0.5629 0.0076 -6.250 -0.2905 0.03421 0.02940 -0.0452 0.5569 0.0078 -6.000 -0.2754 0.03146 0.02641 -0.0437 0.5490 0.0080 -5.750 -0.2563 0.02978 0.02454 -0.0426 0.5410 0.0083 -5.500 -0.2391 0.02711 0.02159 -0.0409 0.5334 0.0086 -5.250 -0.2333 0.01898 0.01238 -0.0361 0.5292 0.0100 -5.000 -0.2112 0.01703 0.01001 -0.0348 0.5213 0.0106 -4.500 -0.1606 0.01613 0.00887 -0.0338 0.5046 0.0113 -4.250 -0.1353 0.01551 0.00808 -0.0332 0.4972 0.0119 -4.000 -0.1096 0.01476 0.00715 -0.0325 0.4904 0.0128 -3.750 -0.0838 0.01425 0.00646 -0.0319 0.4834 0.0138 -3.500 -0.0578 0.01396 0.00614 -0.0316 0.4766 0.0145 -3.250 -0.0318 0.01367 0.00577 -0.0311 0.4695 0.0154 -3.000 -0.0059 0.01328 0.00529 -0.0306 0.4633 0.0163 -2.750 0.0199 0.01293 0.00484 -0.0300 0.4571 0.0172 -2.250 0.0709 0.01232 0.00415 -0.0289 0.4460 0.0196 -2.000 0.0965 0.01207 0.00385 -0.0284 0.4402 0.0206 -1.750 0.1220 0.01185 0.00356 -0.0278 0.4349 0.0216 -1.500 0.1483 0.01170 0.00337 -0.0274 0.4296 0.0226 -1.250 0.1730 0.01139 0.00303 -0.0267 0.4247 0.0241 -1.000 0.1988 0.01125 0.00284 -0.0262 0.4204 0.0252 -0.750 0.2251 0.01111 0.00268 -0.0258 0.4157 0.0265 -0.500 0.2514 0.01103 0.00254 -0.0254 0.4106 0.0281 0.000 0.3040 0.01087 0.00233 -0.0246 0.4024 0.0336 0.250 0.3304 0.01080 0.00227 -0.0242 0.3983 0.0424 0.500 0.3556 0.01063 0.00224 -0.0237 0.3943 0.0993 0.750 0.3521 0.00848 0.00219 -0.0179 0.3917 0.7673 1.000 0.4105 0.00844 0.00256 -0.0237 0.3867 0.9385 1.250 0.4517 0.00869 0.00274 -0.0262 0.3824 0.9596 1.500 0.4942 0.00894 0.00290 -0.0291 0.3784 0.9705 1.750 0.5461 0.00914 0.00301 -0.0341 0.3743 0.9770 2.000 0.5776 0.00921 0.00304 -0.0350 0.3707 0.9795 2.250 0.6062 0.00930 0.00308 -0.0352 0.3671 0.9821 2.500 0.6347 0.00940 0.00313 -0.0354 0.3639 0.9843 2.750 0.6668 0.00948 0.00317 -0.0365 0.3608 0.9855 3.000 0.6987 0.00954 0.00321 -0.0375 0.3575 0.9868 3.250 0.7301 0.00961 0.00327 -0.0384 0.3540 0.9883 3.500 0.7607 0.00971 0.00333 -0.0391 0.3507 0.9900 3.750 0.7904 0.00983 0.00341 -0.0397 0.3478 0.9917 4.000 0.8202 0.00993 0.00351 -0.0403 0.3451 0.9934 4.250 0.8508 0.01001 0.00360 -0.0411 0.3419 0.9948 4.500 0.8818 0.01009 0.00368 -0.0419 0.3384 0.9960 4.750 0.9124 0.01020 0.00379 -0.0428 0.3355 0.9974 5.000 0.9429 0.01034 0.00390 -0.0436 0.3326 0.9988 5.250 0.9738 0.01044 0.00403 -0.0445 0.3296 0.9999 5.500 0.9973 0.01054 0.00417 -0.0438 0.3265 1.0000 5.750 1.0201 0.01067 0.00432 -0.0430 0.3236 1.0000 6.000 1.0426 0.01082 0.00447 -0.0421 0.3205 1.0000 6.250 1.0645 0.01100 0.00465 -0.0411 0.3173 1.0000 6.500 1.0875 0.01112 0.00482 -0.0403 0.3140 1.0000 6.750 1.1100 0.01126 0.00499 -0.0394 0.3100 1.0000 7.000 1.1320 0.01143 0.00518 -0.0385 0.3060 1.0000 7.250 1.1536 0.01163 0.00539 -0.0375 0.3023 1.0000 7.500 1.1760 0.01177 0.00559 -0.0366 0.2983 1.0000 7.750 1.1977 0.01195 0.00579 -0.0357 0.2932 1.0000 8.000 1.2184 0.01217 0.00603 -0.0345 0.2885 1.0000 8.250 1.2404 0.01234 0.00626 -0.0336 0.2839 1.0000 8.500 1.2614 0.01255 0.00650 -0.0326 0.2787 1.0000 8.750 1.2815 0.01280 0.00677 -0.0314 0.2738 1.0000 9.000 1.3025 0.01300 0.00704 -0.0304 0.2677 1.0000 9.250 1.3213 0.01331 0.00734 -0.0290 0.2606 1.0000 9.500 1.3413 0.01355 0.00764 -0.0278 0.2529 1.0000 9.750 1.3594 0.01388 0.00798 -0.0264 0.2457 1.0000 10.000 1.3781 0.01419 0.00833 -0.0250 0.2380 1.0000 10.250 1.3949 0.01457 0.00873 -0.0234 0.2291 1.0000 10.500 1.4099 0.01502 0.00917 -0.0216 0.2186 1.0000 10.750 1.4241 0.01550 0.00965 -0.0196 0.2072 1.0000 11.000 1.4351 0.01610 0.01023 -0.0172 0.1933 1.0000 11.250 1.4429 0.01682 0.01091 -0.0144 0.1780 1.0000 11.500 1.4433 0.01762 0.01166 -0.0102 0.1625 1.0000 11.750 1.4422 0.01854 0.01254 -0.0062 0.1486 1.0000 12.000 1.4375 0.01981 0.01375 -0.0023 0.1320 1.0000 12.250 1.4397 0.02094 0.01490 0.0002 0.1244 1.0000 12.500 1.4352 0.02268 0.01663 0.0027 0.1123 1.0000 12.750 1.4343 0.02449 0.01847 0.0042 0.1043 1.0000 13.000 1.4311 0.02675 0.02076 0.0053 0.0955 1.0000 13.250 1.4238 0.02964 0.02366 0.0059 0.0861 1.0000 13.500 1.4186 0.03255 0.02661 0.0062 0.0802 1.0000 13.750 1.4131 0.03563 0.02976 0.0062 0.0744 1.0000 14.000 1.4036 0.03920 0.03338 0.0061 0.0689 1.0000 14.250 1.3916 0.04313 0.03735 0.0058 0.0622 1.0000 14.500 1.3809 0.04697 0.04125 0.0054 0.0583 1.0000 14.750 1.3743 0.05040 0.04477 0.0051 0.0567 1.0000 15.000 1.3616 0.05456 0.04899 0.0046 0.0520 1.0000 15.250 1.3482 0.05898 0.05344 0.0038 0.0482 1.0000 15.500 1.3400 0.06287 0.05741 0.0031 0.0454 1.0000 15.750 1.3298 0.06710 0.06169 0.0022 0.0421 1.0000 16.000 1.3191 0.07147 0.06612 0.0012 0.0393 1.0000 16.250 1.3121 0.07543 0.07014 0.0003 0.0366 1.0000 16.500 1.3036 0.07964 0.07441 -0.0008 0.0337 1.0000 16.750 1.2941 0.08408 0.07889 -0.0020 0.0309 1.0000 17.000 1.2896 0.08786 0.08275 -0.0030 0.0297 1.0000