XFOIL Version 6.96 Calculated polar for: EPPLER 337 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.2909 0.08689 0.08493 -0.0243 1.0000 0.0159 -9.500 -0.2922 0.08282 0.08089 -0.0255 1.0000 0.0160 -9.250 -0.2936 0.07888 0.07698 -0.0267 1.0000 0.0165 -9.000 -0.2979 0.07439 0.07251 -0.0283 1.0000 0.0165 -8.750 -0.4175 0.07387 0.07179 -0.0366 1.0000 0.0154 -8.500 -0.4265 0.07097 0.06890 -0.0360 1.0000 0.0155 -8.250 -0.4428 0.06781 0.06571 -0.0339 1.0000 0.0155 -8.000 -0.4489 0.06594 0.06386 -0.0314 0.9996 0.0157 -7.750 -0.4105 0.05976 0.05748 -0.0415 0.9200 0.0162 -7.500 -0.3952 0.05588 0.05317 -0.0439 0.8355 0.0166 -7.250 -0.3954 0.05316 0.05016 -0.0415 0.7930 0.0170 -7.000 -0.3936 0.05009 0.04683 -0.0391 0.7647 0.0175 -6.750 -0.3998 0.04352 0.03966 -0.0342 0.7470 0.0192 -6.500 -0.3905 0.04148 0.03748 -0.0325 0.7257 0.0195 -6.250 -0.3789 0.03987 0.03573 -0.0309 0.7061 0.0199 -6.000 -0.3659 0.03818 0.03387 -0.0292 0.6886 0.0204 -5.750 -0.3524 0.03613 0.03159 -0.0272 0.6730 0.0213 -5.500 -0.3438 0.03246 0.02724 -0.0225 0.6610 0.0240 -5.250 -0.3258 0.03068 0.02544 -0.0218 0.6468 0.0246 -5.000 -0.3073 0.02939 0.02403 -0.0206 0.6334 0.0255 -4.750 -0.2882 0.02788 0.02231 -0.0189 0.6208 0.0270 -4.250 -0.2500 0.02416 0.01796 -0.0151 0.5977 0.0309 -4.000 -0.2275 0.02299 0.01664 -0.0140 0.5864 0.0322 -3.750 -0.1960 0.01730 0.00984 -0.0106 0.5783 0.0151 -3.500 -0.1675 0.01549 0.00795 -0.0105 0.5678 0.0145 -3.250 -0.1409 0.01447 0.00678 -0.0100 0.5579 0.0141 -3.000 -0.1157 0.01371 0.00591 -0.0092 0.5478 0.0139 -2.750 -0.0914 0.01312 0.00525 -0.0083 0.5381 0.0139 -2.500 -0.0682 0.01265 0.00467 -0.0072 0.5293 0.0143 -2.250 -0.0442 0.01224 0.00422 -0.0062 0.5205 0.0147 -2.000 -0.0215 0.01184 0.00374 -0.0050 0.5127 0.0160 -1.750 0.0032 0.01157 0.00345 -0.0043 0.5043 0.0182 -1.500 0.0258 0.01118 0.00306 -0.0030 0.4971 0.0350 -1.250 0.0471 0.01065 0.00287 -0.0018 0.4894 0.1206 -1.000 0.0446 0.00879 0.00256 0.0035 0.4841 0.5512 -0.750 0.0474 0.00831 0.00328 0.0101 0.4789 0.8830 -0.500 0.0796 0.00933 0.00425 0.0110 0.4717 0.9150 -0.250 0.1537 0.01037 0.00510 0.0027 0.4626 0.9256 0.000 0.2269 0.01111 0.00567 -0.0059 0.4536 0.9363 0.250 0.2922 0.01163 0.00605 -0.0131 0.4460 0.9454 0.500 0.3250 0.01169 0.00604 -0.0140 0.4399 0.9502 0.750 0.3592 0.01171 0.00593 -0.0155 0.4342 0.9516 1.000 0.3924 0.01166 0.00585 -0.0167 0.4287 0.9533 1.250 0.4228 0.01166 0.00579 -0.0173 0.4236 0.9555 1.500 0.4496 0.01174 0.00577 -0.0172 0.4187 0.9581 1.750 0.4656 0.01183 0.00587 -0.0148 0.4148 0.9624 2.000 0.4995 0.01174 0.00574 -0.0163 0.4098 0.9633 2.250 0.5322 0.01173 0.00566 -0.0175 0.4053 0.9645 2.500 0.5636 0.01172 0.00562 -0.0184 0.4008 0.9657 2.750 0.5938 0.01170 0.00560 -0.0191 0.3964 0.9672 3.000 0.6226 0.01172 0.00558 -0.0194 0.3922 0.9689 3.250 0.6485 0.01183 0.00563 -0.0193 0.3881 0.9706 3.500 0.6728 0.01185 0.00568 -0.0187 0.3842 0.9727 3.750 0.6930 0.01194 0.00578 -0.0173 0.3805 0.9749 4.000 0.7239 0.01192 0.00573 -0.0181 0.3766 0.9756 4.250 0.7544 0.01199 0.00575 -0.0190 0.3722 0.9766 4.500 0.7842 0.01196 0.00577 -0.0196 0.3685 0.9776 4.750 0.8118 0.01197 0.00580 -0.0198 0.3644 0.9785 5.000 0.8393 0.01204 0.00586 -0.0200 0.3605 0.9796 5.250 0.8661 0.01217 0.00596 -0.0201 0.3567 0.9809 5.500 0.8915 0.01219 0.00605 -0.0198 0.3528 0.9820 5.750 0.9158 0.01224 0.00614 -0.0193 0.3485 0.9830 6.000 0.9391 0.01237 0.00624 -0.0187 0.3442 0.9844 6.250 0.9603 0.01251 0.00641 -0.0176 0.3400 0.9856 6.500 0.9880 0.01251 0.00648 -0.0179 0.3355 0.9861 6.750 1.0151 0.01257 0.00655 -0.0180 0.3312 0.9867 7.000 1.0425 0.01273 0.00669 -0.0183 0.3269 0.9874 7.250 1.0706 0.01275 0.00681 -0.0187 0.3224 0.9883 7.500 1.0962 0.01281 0.00692 -0.0186 0.3169 0.9890 7.750 1.1203 0.01298 0.00708 -0.0182 0.3117 0.9898 8.000 1.1453 0.01303 0.00724 -0.0180 0.3064 0.9905 8.250 1.1691 0.01316 0.00738 -0.0176 0.3007 0.9913 8.500 1.1941 0.01331 0.00758 -0.0174 0.2948 0.9923 8.750 1.2179 0.01342 0.00777 -0.0170 0.2884 0.9932 9.000 1.2395 0.01362 0.00798 -0.0162 0.2817 0.9940 9.250 1.2617 0.01377 0.00821 -0.0155 0.2747 0.9947 9.500 1.2860 0.01398 0.00844 -0.0153 0.2672 0.9953 9.750 1.3103 0.01417 0.00869 -0.0152 0.2583 0.9960 10.000 1.3340 0.01441 0.00897 -0.0149 0.2489 0.9968 10.250 1.3581 0.01473 0.00931 -0.0149 0.2385 0.9979 10.500 1.3799 0.01512 0.00970 -0.0144 0.2267 0.9989 10.750 1.4003 0.01557 0.01016 -0.0138 0.2135 0.9997 11.000 1.4142 0.01607 0.01066 -0.0119 0.2003 1.0000 11.250 1.4233 0.01660 0.01119 -0.0090 0.1880 1.0000 11.500 1.4295 0.01717 0.01175 -0.0057 0.1762 1.0000 11.750 1.4316 0.01778 0.01237 -0.0017 0.1649 1.0000 12.000 1.4279 0.01841 0.01300 0.0032 0.1550 1.0000 12.250 1.4098 0.01888 0.01348 0.0110 0.1487 1.0000 12.500 1.3906 0.01937 0.01400 0.0186 0.1438 1.0000 12.750 1.3707 0.01999 0.01466 0.0258 0.1382 1.0000 13.000 1.3600 0.02105 0.01573 0.0304 0.1316 1.0000 13.250 1.3544 0.02262 0.01728 0.0331 0.1226 1.0000 13.500 1.3511 0.02447 0.01916 0.0347 0.1142 1.0000 13.750 1.3480 0.02661 0.02133 0.0357 0.1066 1.0000 14.000 1.3437 0.02908 0.02384 0.0364 0.1001 1.0000 14.250 1.3367 0.03199 0.02678 0.0367 0.0930 1.0000 14.500 1.3293 0.03509 0.02991 0.0368 0.0873 1.0000 14.750 1.3227 0.03820 0.03309 0.0367 0.0819 1.0000 15.000 1.3122 0.04181 0.03673 0.0364 0.0772 1.0000 15.250 1.3035 0.04529 0.04029 0.0360 0.0731 1.0000 15.500 1.2947 0.04884 0.04390 0.0356 0.0691 1.0000 15.750 1.2802 0.05313 0.04824 0.0348 0.0651 1.0000 16.000 1.2736 0.05669 0.05188 0.0341 0.0619 1.0000 16.250 1.2634 0.06073 0.05598 0.0331 0.0585 1.0000 16.750 1.2440 0.06907 0.06444 0.0308 0.0520 1.0000 17.000 1.2337 0.07346 0.06887 0.0295 0.0492 1.0000 17.250 1.2201 0.07838 0.07383 0.0279 0.0463 1.0000 17.500 1.2159 0.08213 0.07767 0.0267 0.0438 1.0000 17.750 1.2077 0.08646 0.08205 0.0251 0.0414 1.0000 18.000 1.1963 0.09135 0.08697 0.0233 0.0391 1.0000