XFOIL Version 6.96 Calculated polar for: EPPLER 331 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.3825 0.08839 0.08644 -0.0052 1.0000 0.0127 -9.000 -0.3843 0.08389 0.08197 -0.0069 1.0000 0.0129 -8.750 -0.3875 0.07924 0.07734 -0.0088 1.0000 0.0130 -8.500 -0.3927 0.07438 0.07250 -0.0111 1.0000 0.0130 -8.250 -0.4021 0.06907 0.06722 -0.0143 1.0000 0.0131 -8.000 -0.4199 0.06341 0.06154 -0.0184 1.0000 0.0129 -7.750 -0.4370 0.05903 0.05714 -0.0191 1.0000 0.0128 -7.500 -0.4523 0.05534 0.05342 -0.0177 1.0000 0.0129 -7.250 -0.4594 0.05134 0.04937 -0.0167 1.0000 0.0129 -7.000 -0.4496 0.04574 0.04354 -0.0190 0.8953 0.0133 -6.750 -0.4527 0.04237 0.03985 -0.0165 0.8359 0.0135 -6.500 -0.4516 0.03850 0.03570 -0.0143 0.8028 0.0140 -6.000 -0.4565 0.03997 0.03622 -0.0098 0.8100 0.0151 -5.750 -0.4461 0.03810 0.03419 -0.0082 0.7791 0.0154 -5.500 -0.4326 0.03634 0.03222 -0.0065 0.7541 0.0158 -5.250 -0.4176 0.03433 0.02998 -0.0046 0.7320 0.0165 -5.000 -0.4041 0.03048 0.02541 -0.0003 0.7155 0.0189 -4.750 -0.3862 0.02859 0.02343 0.0007 0.6969 0.0193 -4.500 -0.3669 0.02717 0.02185 0.0020 0.6798 0.0202 -4.250 -0.3481 0.02491 0.01904 0.0048 0.6653 0.0235 -4.000 -0.3262 0.02346 0.01753 0.0055 0.6500 0.0246 -3.750 -0.2992 0.01816 0.01135 0.0090 0.6386 0.0144 -3.500 -0.2724 0.01635 0.00927 0.0098 0.6247 0.0138 -3.250 -0.2451 0.01514 0.00785 0.0104 0.6114 0.0137 -3.000 -0.2185 0.01454 0.00705 0.0110 0.5983 0.0145 -2.750 -0.1919 0.01384 0.00622 0.0116 0.5854 0.0148 -2.500 -0.1670 0.01297 0.00528 0.0125 0.5732 0.0146 -2.250 -0.1430 0.01237 0.00460 0.0134 0.5621 0.0146 -2.000 -0.1191 0.01190 0.00404 0.0145 0.5513 0.0149 -1.750 -0.0959 0.01136 0.00346 0.0156 0.5406 0.0156 -1.500 -0.0713 0.01106 0.00309 0.0164 0.5303 0.0175 -1.250 -0.0467 0.01075 0.00272 0.0173 0.5205 0.0245 -1.000 -0.0346 0.00929 0.00237 0.0200 0.5123 0.3202 -0.750 -0.0402 0.00741 0.00260 0.0275 0.5057 0.8786 -0.500 0.0388 0.00917 0.00423 0.0194 0.4921 0.9339 -0.250 0.0974 0.00981 0.00470 0.0137 0.4810 0.9444 0.000 0.1681 0.01046 0.00517 0.0054 0.4695 0.9545 0.250 0.2179 0.01061 0.00519 0.0010 0.4596 0.9605 0.500 0.2538 0.01060 0.00509 -0.0007 0.4515 0.9628 0.750 0.2847 0.01061 0.00501 -0.0014 0.4437 0.9653 1.000 0.3120 0.01064 0.00499 -0.0014 0.4367 0.9684 1.250 0.3363 0.01071 0.00499 -0.0007 0.4300 0.9716 1.500 0.3705 0.01064 0.00485 -0.0022 0.4233 0.9728 1.750 0.4034 0.01057 0.00474 -0.0034 0.4160 0.9741 2.000 0.4349 0.01058 0.00467 -0.0044 0.4098 0.9757 2.250 0.4653 0.01055 0.00463 -0.0050 0.4035 0.9775 2.500 0.4939 0.01058 0.00461 -0.0053 0.3975 0.9795 2.750 0.5204 0.01064 0.00465 -0.0052 0.3917 0.9817 3.000 0.5463 0.01070 0.00471 -0.0050 0.3861 0.9837 3.500 0.6094 0.01062 0.00458 -0.0069 0.3742 0.9858 3.750 0.6399 0.01062 0.00455 -0.0077 0.3683 0.9870 4.000 0.6689 0.01066 0.00459 -0.0082 0.3627 0.9882 4.250 0.6979 0.01066 0.00461 -0.0086 0.3568 0.9896 4.500 0.7260 0.01073 0.00465 -0.0089 0.3509 0.9910 4.750 0.7534 0.01078 0.00474 -0.0090 0.3453 0.9922 5.000 0.7804 0.01084 0.00482 -0.0090 0.3394 0.9935 5.250 0.8095 0.01092 0.00487 -0.0096 0.3334 0.9945 5.500 0.8390 0.01090 0.00492 -0.0102 0.3272 0.9954 5.750 0.8669 0.01098 0.00499 -0.0105 0.3209 0.9962 6.000 0.8954 0.01101 0.00508 -0.0109 0.3143 0.9971 6.250 0.9243 0.01108 0.00516 -0.0114 0.3071 0.9982 6.500 0.9526 0.01116 0.00528 -0.0118 0.3004 0.9991 6.750 0.9801 0.01126 0.00540 -0.0120 0.2924 0.9998 7.000 1.0046 0.01138 0.00557 -0.0116 0.2852 1.0000 7.250 1.0276 0.01154 0.00575 -0.0109 0.2773 1.0000 7.500 1.0508 0.01168 0.00595 -0.0103 0.2690 1.0000 7.750 1.0731 0.01190 0.00617 -0.0095 0.2601 1.0000 8.000 1.0960 0.01205 0.00639 -0.0088 0.2507 1.0000 8.250 1.1181 0.01227 0.00663 -0.0080 0.2404 1.0000 8.500 1.1396 0.01254 0.00691 -0.0072 0.2290 1.0000 8.750 1.1606 0.01285 0.00722 -0.0062 0.2165 1.0000 9.000 1.1811 0.01319 0.00757 -0.0052 0.2027 1.0000 9.250 1.2007 0.01358 0.00796 -0.0042 0.1874 1.0000 9.500 1.2192 0.01405 0.00840 -0.0029 0.1699 1.0000 9.750 1.2363 0.01461 0.00892 -0.0015 0.1524 1.0000 10.000 1.2518 0.01526 0.00952 0.0001 0.1359 1.0000 10.250 1.2664 0.01591 0.01015 0.0019 0.1203 1.0000 10.500 1.2794 0.01662 0.01083 0.0039 0.1057 1.0000 10.750 1.2906 0.01736 0.01156 0.0062 0.0926 1.0000 11.000 1.2994 0.01816 0.01233 0.0088 0.0805 1.0000 11.250 1.3059 0.01898 0.01314 0.0118 0.0709 1.0000 11.500 1.3083 0.01986 0.01400 0.0154 0.0622 1.0000 11.750 1.3086 0.02063 0.01480 0.0193 0.0551 1.0000 12.000 1.3033 0.02141 0.01560 0.0242 0.0500 1.0000 12.250 1.2848 0.02200 0.01623 0.0315 0.0473 1.0000 12.500 1.2705 0.02292 0.01721 0.0372 0.0458 1.0000 12.750 1.2618 0.02434 0.01868 0.0406 0.0420 1.0000 13.000 1.2562 0.02621 0.02057 0.0425 0.0378 1.0000 13.250 1.2525 0.02837 0.02279 0.0434 0.0336 1.0000 13.500 1.2480 0.03097 0.02550 0.0439 0.0326 1.0000 13.750 1.2396 0.03419 0.02874 0.0437 0.0293 1.0000 14.000 1.2377 0.03686 0.03152 0.0435 0.0269 1.0000 14.250 1.2308 0.04018 0.03488 0.0430 0.0249 1.0000 14.500 1.2223 0.04377 0.03855 0.0424 0.0232 1.0000 14.750 1.2129 0.04756 0.04246 0.0416 0.0226 1.0000 15.000 1.2050 0.05120 0.04619 0.0408 0.0212 1.0000 15.250 1.1933 0.05538 0.05045 0.0398 0.0203 1.0000 15.500 1.1796 0.05990 0.05505 0.0385 0.0198 1.0000 15.750 1.1684 0.06432 0.05957 0.0372 0.0187 1.0000 16.000 1.1669 0.06753 0.06284 0.0361 0.0168 1.0000 16.250 1.1564 0.07206 0.06744 0.0346 0.0162 1.0000 16.500 1.1439 0.07700 0.07245 0.0328 0.0155 1.0000 16.750 1.1366 0.08127 0.07682 0.0313 0.0146 1.0000 17.000 1.1299 0.08555 0.08118 0.0297 0.0137 1.0000 17.250 1.1170 0.09084 0.08658 0.0276 0.0136 1.0000 17.500 1.1107 0.09520 0.09099 0.0259 0.0128 1.0000