XFOIL Version 6.96 Calculated polar for: EPPLER 333 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.3573 0.09438 0.09282 -0.0213 1.0000 0.0072 -9.000 -0.3554 0.09076 0.08923 -0.0229 1.0000 0.0072 -8.750 -0.3539 0.08730 0.08578 -0.0244 1.0000 0.0072 -8.500 -0.2523 0.06550 0.06347 -0.0376 0.7849 0.0074 -8.250 -0.2563 0.06157 0.05947 -0.0392 0.7609 0.0075 -8.000 -0.2655 0.05694 0.05478 -0.0420 0.7426 0.0075 -7.750 -0.2806 0.05251 0.05029 -0.0452 0.7264 0.0075 -7.500 -0.2950 0.04895 0.04665 -0.0449 0.7111 0.0075 -7.250 -0.3010 0.04504 0.04263 -0.0448 0.6972 0.0074 -7.000 -0.3032 0.04145 0.03895 -0.0444 0.6831 0.0075 -6.750 -0.3011 0.03798 0.03536 -0.0439 0.6701 0.0076 -6.500 -0.2965 0.03450 0.03176 -0.0433 0.6581 0.0077 -6.250 -0.2896 0.03119 0.02833 -0.0425 0.6462 0.0078 -6.000 -0.2801 0.02817 0.02518 -0.0417 0.6349 0.0080 -5.750 -0.2834 0.04039 0.03698 -0.0434 0.6462 0.0079 -5.500 -0.2689 0.03784 0.03426 -0.0421 0.6338 0.0082 -5.250 -0.2536 0.03510 0.03133 -0.0405 0.6221 0.0086 -5.000 -0.2372 0.03218 0.02817 -0.0387 0.6105 0.0091 -4.750 -0.2149 0.02873 0.02440 -0.0361 0.6002 0.0100 -4.500 -0.2064 0.02349 0.01866 -0.0326 0.5922 0.0105 -4.250 -0.1856 0.02226 0.01728 -0.0316 0.5814 0.0107 -4.000 -0.1636 0.02116 0.01602 -0.0307 0.5707 0.0112 -3.750 -0.1402 0.01971 0.01433 -0.0294 0.5605 0.0127 -3.500 -0.1186 0.01741 0.01161 -0.0276 0.5509 0.0144 -3.250 -0.0927 0.01447 0.00818 -0.0256 0.5422 0.0102 -3.000 -0.0671 0.01301 0.00658 -0.0249 0.5332 0.0096 -2.750 -0.0410 0.01227 0.00570 -0.0243 0.5237 0.0097 -2.500 -0.0138 0.01217 0.00550 -0.0239 0.5145 0.0101 -2.250 0.0111 0.01122 0.00445 -0.0231 0.5059 0.0099 -2.000 0.0355 0.01052 0.00369 -0.0222 0.4977 0.0098 -1.750 0.0601 0.01007 0.00315 -0.0214 0.4901 0.0098 -1.500 0.0854 0.00975 0.00276 -0.0207 0.4821 0.0098 -1.250 0.1110 0.00949 0.00244 -0.0201 0.4746 0.0100 -1.000 0.1365 0.00919 0.00207 -0.0195 0.4671 0.0109 -0.750 0.1628 0.00906 0.00189 -0.0190 0.4604 0.0136 -0.500 0.1880 0.00876 0.00171 -0.0184 0.4537 0.0527 -0.250 0.2128 0.00852 0.00166 -0.0178 0.4468 0.1270 0.000 0.2124 0.00631 0.00146 -0.0129 0.4425 0.7487 0.250 0.2275 0.00622 0.00180 -0.0093 0.4368 0.9052 0.500 0.2485 0.00647 0.00204 -0.0072 0.4312 0.9274 0.750 0.2726 0.00661 0.00214 -0.0060 0.4256 0.9364 1.000 0.2946 0.00682 0.00230 -0.0042 0.4199 0.9467 1.250 0.3244 0.00707 0.00252 -0.0040 0.4147 0.9552 1.500 0.3483 0.00721 0.00261 -0.0029 0.4097 0.9615 1.750 0.3945 0.00746 0.00276 -0.0067 0.4029 0.9642 2.000 0.4254 0.00748 0.00276 -0.0074 0.3985 0.9650 2.250 0.4553 0.00753 0.00276 -0.0079 0.3934 0.9658 2.500 0.4846 0.00761 0.00278 -0.0083 0.3878 0.9666 2.750 0.5140 0.00763 0.00279 -0.0087 0.3838 0.9675 3.000 0.5427 0.00768 0.00281 -0.0090 0.3791 0.9685 3.250 0.5694 0.00776 0.00284 -0.0089 0.3741 0.9699 3.500 0.5943 0.00779 0.00286 -0.0083 0.3705 0.9714 3.750 0.6106 0.00780 0.00287 -0.0059 0.3665 0.9746 4.000 0.6399 0.00787 0.00291 -0.0063 0.3618 0.9752 4.250 0.6699 0.00795 0.00296 -0.0070 0.3573 0.9756 4.500 0.7005 0.00799 0.00301 -0.0077 0.3531 0.9761 4.750 0.7307 0.00807 0.00307 -0.0084 0.3482 0.9765 5.000 0.7605 0.00819 0.00316 -0.0091 0.3433 0.9771 5.250 0.7910 0.00824 0.00323 -0.0098 0.3390 0.9776 5.500 0.8212 0.00833 0.00331 -0.0105 0.3338 0.9783 5.750 0.8506 0.00846 0.00342 -0.0111 0.3288 0.9790 6.000 0.8799 0.00852 0.00351 -0.0116 0.3242 0.9798 6.250 0.9081 0.00863 0.00361 -0.0119 0.3186 0.9807 6.500 0.9357 0.00874 0.00373 -0.0122 0.3133 0.9818 6.750 0.9630 0.00883 0.00383 -0.0123 0.3075 0.9830 7.000 0.9877 0.00897 0.00396 -0.0119 0.3020 0.9846 7.250 1.0120 0.00906 0.00409 -0.0114 0.2968 0.9862 7.500 1.0422 0.00921 0.00423 -0.0122 0.2899 0.9867 7.750 1.0725 0.00935 0.00438 -0.0131 0.2826 0.9872 8.000 1.1024 0.00955 0.00457 -0.0140 0.2742 0.9878 8.250 1.1324 0.00970 0.00474 -0.0148 0.2660 0.9886 8.500 1.1612 0.00993 0.00496 -0.0154 0.2573 0.9894 8.750 1.1893 0.01016 0.00518 -0.0160 0.2472 0.9904 9.000 1.2171 0.01040 0.00542 -0.0164 0.2367 0.9914 9.250 1.2439 0.01069 0.00570 -0.0168 0.2253 0.9927 9.500 1.2696 0.01102 0.00600 -0.0169 0.2127 0.9941 9.750 1.2949 0.01144 0.00637 -0.0171 0.1963 0.9954 10.000 1.3217 0.01192 0.00680 -0.0177 0.1801 0.9965 10.250 1.3476 0.01246 0.00727 -0.0181 0.1632 0.9978 10.500 1.3725 0.01308 0.00782 -0.0185 0.1441 0.9992 10.750 1.3859 0.01381 0.00843 -0.0166 0.1237 1.0000 11.000 1.3899 0.01419 0.00881 -0.0125 0.1162 1.0000 11.250 1.3913 0.01462 0.00922 -0.0080 0.1069 1.0000 11.500 1.3985 0.01515 0.00973 -0.0047 0.0974 1.0000 11.750 1.4043 0.01594 0.01044 -0.0015 0.0827 1.0000 12.000 1.4123 0.01652 0.01102 0.0013 0.0764 1.0000 12.250 1.4170 0.01730 0.01176 0.0045 0.0678 1.0000 12.500 1.4212 0.01819 0.01264 0.0074 0.0591 1.0000 12.750 1.4268 0.01910 0.01356 0.0098 0.0529 1.0000 13.000 1.4278 0.02035 0.01479 0.0123 0.0457 1.0000 13.250 1.4275 0.02187 0.01631 0.0144 0.0393 1.0000 13.500 1.4338 0.02315 0.01766 0.0156 0.0380 1.0000 13.750 1.4355 0.02491 0.01947 0.0167 0.0337 1.0000 14.000 1.4343 0.02711 0.02170 0.0175 0.0301 1.0000 14.250 1.4364 0.02919 0.02384 0.0179 0.0278 1.0000 14.500 1.4327 0.03194 0.02665 0.0181 0.0249 1.0000 14.750 1.4307 0.03465 0.02942 0.0180 0.0229 1.0000 15.000 1.4290 0.03742 0.03227 0.0179 0.0214 1.0000 15.500 1.4138 0.04442 0.03938 0.0171 0.0172 1.0000 15.750 1.4090 0.04769 0.04275 0.0166 0.0168 1.0000 16.000 1.3999 0.05152 0.04664 0.0158 0.0153 1.0000 16.250 1.3920 0.05534 0.05054 0.0150 0.0146 1.0000 16.500 1.3814 0.05961 0.05488 0.0139 0.0135 1.0000 16.750 1.3750 0.06347 0.05882 0.0129 0.0126 1.0000 17.000 1.3672 0.06758 0.06303 0.0117 0.0120 1.0000 17.250 1.3593 0.07178 0.06729 0.0103 0.0113 1.0000 17.500 1.3509 0.07619 0.07179 0.0089 0.0109 1.0000 17.750 1.3416 0.08077 0.07644 0.0073 0.0103 1.0000 18.000 1.3324 0.08543 0.08120 0.0055 0.0100 1.0000 18.250 1.3266 0.08967 0.08551 0.0039 0.0090 1.0000 18.500 1.3197 0.09416 0.09008 0.0021 0.0087 1.0000 18.750 1.3123 0.09877 0.09479 0.0003 0.0085 1.0000 19.000 1.3035 0.10370 0.09977 -0.0019 0.0078 1.0000 19.250 1.2949 0.10867 0.10483 -0.0041 0.0075 1.0000