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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.000 -0.3262 0.06021 0.05686 -0.0460 0.6685 0.0089 -6.500 -0.3213 0.05090 0.04718 -0.0451 0.6463 0.0068 -6.250 -0.3129 0.04761 0.04372 -0.0442 0.6350 0.0065 -6.000 -0.3038 0.04377 0.03967 -0.0428 0.6251 0.0063 -5.750 -0.2926 0.04011 0.03577 -0.0412 0.6149 0.0059 -5.500 -0.2809 0.03597 0.03133 -0.0391 0.6052 0.0058 -5.250 -0.2672 0.03215 0.02719 -0.0368 0.5961 0.0059 -5.000 -0.2516 0.02846 0.02314 -0.0344 0.5867 0.0061 -4.750 -0.2349 0.02467 0.01894 -0.0319 0.5778 0.0061 -4.500 -0.2164 0.02089 0.01465 -0.0294 0.5693 0.0064 -4.250 -0.1941 0.01841 0.01174 -0.0278 0.5606 0.0067 -4.000 -0.1691 0.01712 0.01008 -0.0268 0.5510 0.0072 -3.750 -0.1438 0.01608 0.00878 -0.0260 0.5414 0.0073 -3.500 -0.1183 0.01512 0.00761 -0.0253 0.5322 0.0073 -3.250 -0.0930 0.01420 0.00652 -0.0246 0.5232 0.0073 -3.000 -0.0678 0.01343 0.00563 -0.0239 0.5150 0.0074 -2.750 -0.0431 0.01287 0.00495 -0.0232 0.5069 0.0075 -2.500 -0.0183 0.01236 0.00438 -0.0225 0.4987 0.0076 -2.250 0.0064 0.01198 0.00392 -0.0217 0.4908 0.0079 -2.000 0.0317 0.01166 0.00355 -0.0211 0.4833 0.0082 -1.750 0.0570 0.01141 0.00323 -0.0205 0.4763 0.0087 -1.500 0.0829 0.01120 0.00296 -0.0200 0.4689 0.0092 -1.250 0.1086 0.01103 0.00271 -0.0195 0.4620 0.0102 -1.000 0.1346 0.01084 0.00249 -0.0190 0.4553 0.0133 -0.750 0.1603 0.01068 0.00234 -0.0185 0.4491 0.0248 -0.500 0.1859 0.01049 0.00224 -0.0180 0.4431 0.0522 -0.250 0.2094 0.01010 0.00216 -0.0173 0.4368 0.1572 0.000 0.2014 0.00781 0.00231 -0.0100 0.4330 0.8651 0.250 0.2241 0.00797 0.00243 -0.0085 0.4278 0.9025 0.500 0.2485 0.00816 0.00257 -0.0072 0.4221 0.9202 0.750 0.2741 0.00843 0.00278 -0.0061 0.4169 0.9364 1.000 0.2998 0.00861 0.00290 -0.0052 0.4114 0.9467 1.250 0.3412 0.00886 0.00306 -0.0077 0.4056 0.9525 1.500 0.3707 0.00894 0.00306 -0.0081 0.4008 0.9543 1.750 0.3979 0.00898 0.00305 -0.0080 0.3957 0.9559 2.000 0.4236 0.00903 0.00304 -0.0076 0.3907 0.9577 2.250 0.4472 0.00908 0.00304 -0.0067 0.3867 0.9599 2.500 0.4710 0.00911 0.00304 -0.0059 0.3822 0.9617 2.750 0.5006 0.00918 0.00306 -0.0064 0.3771 0.9624 3.000 0.5298 0.00928 0.00310 -0.0068 0.3729 0.9632 3.250 0.5589 0.00933 0.00315 -0.0072 0.3686 0.9640 3.500 0.5875 0.00941 0.00320 -0.0075 0.3636 0.9648 3.750 0.6157 0.00951 0.00326 -0.0077 0.3594 0.9657 4.000 0.6440 0.00959 0.00334 -0.0079 0.3551 0.9667 4.250 0.6723 0.00967 0.00342 -0.0082 0.3504 0.9678 4.500 0.6997 0.00978 0.00350 -0.0083 0.3459 0.9692 4.750 0.7264 0.00988 0.00359 -0.0082 0.3419 0.9706 5.000 0.7523 0.00996 0.00370 -0.0080 0.3372 0.9721 5.250 0.7760 0.01007 0.00380 -0.0073 0.3325 0.9740 5.500 0.8032 0.01019 0.00391 -0.0074 0.3279 0.9751 5.750 0.8327 0.01030 0.00405 -0.0080 0.3229 0.9758 6.000 0.8617 0.01044 0.00419 -0.0085 0.3174 0.9766 6.250 0.8909 0.01058 0.00435 -0.0091 0.3124 0.9774 6.500 0.9203 0.01072 0.00451 -0.0097 0.3063 0.9783 6.750 0.9489 0.01090 0.00469 -0.0101 0.3001 0.9794 7.000 0.9772 0.01104 0.00487 -0.0106 0.2938 0.9806 7.250 1.0041 0.01124 0.00507 -0.0107 0.2869 0.9819 7.500 1.0311 0.01140 0.00527 -0.0109 0.2802 0.9834 7.750 1.0560 0.01162 0.00549 -0.0107 0.2729 0.9852 8.000 1.0832 0.01181 0.00572 -0.0109 0.2648 0.9865 8.250 1.1117 0.01207 0.00599 -0.0116 0.2555 0.9873 8.500 1.1394 0.01237 0.00629 -0.0121 0.2451 0.9884 8.750 1.1667 0.01267 0.00660 -0.0125 0.2336 0.9897 9.000 1.1933 0.01301 0.00695 -0.0129 0.2222 0.9913 9.250 1.2189 0.01339 0.00733 -0.0131 0.2099 0.9932 9.500 1.2437 0.01384 0.00777 -0.0132 0.1960 0.9953 9.750 1.2689 0.01439 0.00828 -0.0135 0.1802 0.9973 10.000 1.2932 0.01496 0.00882 -0.0138 0.1659 0.9996 10.250 1.3037 0.01546 0.00932 -0.0111 0.1537 1.0000 10.500 1.3094 0.01599 0.00982 -0.0075 0.1413 1.0000 10.750 1.3169 0.01653 0.01034 -0.0043 0.1304 1.0000 11.000 1.3252 0.01717 0.01096 -0.0015 0.1190 1.0000 11.250 1.3322 0.01783 0.01161 0.0015 0.1093 1.0000 11.500 1.3369 0.01859 0.01236 0.0047 0.0996 1.0000 11.750 1.3421 0.01945 0.01320 0.0075 0.0905 1.0000 12.000 1.3472 0.02040 0.01418 0.0099 0.0816 1.0000 12.250 1.3514 0.02151 0.01531 0.0121 0.0747 1.0000 12.750 1.3571 0.02433 0.01820 0.0155 0.0623 1.0000 13.000 1.3561 0.02631 0.02019 0.0166 0.0560 1.0000 13.250 1.3591 0.02817 0.02213 0.0173 0.0522 1.0000 13.500 1.3588 0.03047 0.02449 0.0177 0.0486 1.0000 13.750 1.3584 0.03292 0.02701 0.0179 0.0451 1.0000 14.000 1.3566 0.03562 0.02979 0.0179 0.0418 1.0000 14.250 1.3514 0.03877 0.03299 0.0177 0.0387 1.0000 14.500 1.3488 0.04172 0.03605 0.0174 0.0366 1.0000 14.750 1.3437 0.04501 0.03941 0.0169 0.0340 1.0000 15.000 1.3372 0.04850 0.04299 0.0163 0.0321 1.0000 15.250 1.3252 0.05271 0.04722 0.0155 0.0274 1.0000 15.500 1.3214 0.05604 0.05067 0.0148 0.0274 1.0000 15.750 1.3153 0.05976 0.05449 0.0139 0.0265 1.0000 16.000 1.3045 0.06419 0.05897 0.0126 0.0241 1.0000 16.250 1.2980 0.06819 0.06306 0.0115 0.0232 1.0000 16.500 1.2919 0.07220 0.06716 0.0102 0.0217 1.0000 16.750 1.2797 0.07714 0.07212 0.0085 0.0184 1.0000 17.000 1.2746 0.08121 0.07630 0.0071 0.0184 1.0000 17.250 1.2660 0.08581 0.08096 0.0054 0.0161 1.0000 17.500 1.2612 0.09001 0.08527 0.0038 0.0162 1.0000 17.750 1.2532 0.09470 0.09002 0.0019 0.0146 1.0000 18.000 1.2480 0.09903 0.09446 0.0002 0.0146 1.0000