XFOIL Version 6.96 Calculated polar for: EPPLER 329 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.2440 0.08830 0.08573 -0.0621 0.7593 0.0075 -9.750 -0.2461 0.08475 0.08205 -0.0631 0.7235 0.0076 -6.750 -0.3656 0.02384 0.01905 -0.0511 0.6002 0.0041 -6.500 -0.3569 0.01954 0.01414 -0.0479 0.5913 0.0040 -6.250 -0.3382 0.01737 0.01159 -0.0463 0.5817 0.0040 -6.000 -0.3159 0.01617 0.01014 -0.0453 0.5718 0.0040 -5.750 -0.2927 0.01515 0.00892 -0.0444 0.5612 0.0040 -5.500 -0.2686 0.01437 0.00797 -0.0436 0.5519 0.0040 -5.250 -0.2445 0.01366 0.00711 -0.0429 0.5428 0.0040 -5.000 -0.2203 0.01299 0.00630 -0.0421 0.5343 0.0040 -4.750 -0.1958 0.01255 0.00575 -0.0415 0.5246 0.0040 -4.500 -0.1712 0.01209 0.00520 -0.0408 0.5163 0.0041 -4.250 -0.1466 0.01174 0.00476 -0.0401 0.5080 0.0041 -4.000 -0.1217 0.01139 0.00435 -0.0395 0.5005 0.0041 -3.750 -0.0970 0.01108 0.00396 -0.0388 0.4930 0.0042 -3.500 -0.0719 0.01080 0.00363 -0.0383 0.4856 0.0042 -3.000 -0.0219 0.01027 0.00298 -0.0371 0.4711 0.0046 -2.750 0.0039 0.01011 0.00277 -0.0366 0.4643 0.0050 -2.500 0.0300 0.00997 0.00260 -0.0362 0.4583 0.0053 -2.250 0.0562 0.00985 0.00244 -0.0359 0.4518 0.0058 -2.000 0.0822 0.00974 0.00230 -0.0355 0.4451 0.0070 -1.750 0.1088 0.00963 0.00217 -0.0352 0.4394 0.0086 -1.500 0.1353 0.00955 0.00207 -0.0349 0.4337 0.0112 -1.250 0.1617 0.00946 0.00199 -0.0346 0.4284 0.0174 -1.000 0.1883 0.00936 0.00191 -0.0344 0.4232 0.0274 -0.750 0.2137 0.00919 0.00186 -0.0340 0.4175 0.0645 -0.500 0.2386 0.00896 0.00180 -0.0335 0.4125 0.1309 -0.250 0.2389 0.00672 0.00155 -0.0291 0.4095 0.7421 0.000 0.2642 0.00674 0.00167 -0.0283 0.4048 0.7981 0.250 0.2910 0.00684 0.00174 -0.0280 0.3995 0.8152 0.500 0.3186 0.00692 0.00179 -0.0278 0.3953 0.8242 0.750 0.3459 0.00700 0.00185 -0.0276 0.3908 0.8321 1.000 0.3729 0.00712 0.00193 -0.0273 0.3863 0.8408 1.250 0.4008 0.00720 0.00195 -0.0274 0.3818 0.8428 1.500 0.4290 0.00725 0.00196 -0.0275 0.3779 0.8438 1.750 0.4570 0.00730 0.00198 -0.0276 0.3740 0.8448 2.000 0.4847 0.00737 0.00201 -0.0276 0.3695 0.8457 2.250 0.5126 0.00743 0.00204 -0.0276 0.3658 0.8467 2.500 0.5406 0.00749 0.00208 -0.0277 0.3621 0.8476 2.750 0.5683 0.00756 0.00213 -0.0278 0.3583 0.8486 3.000 0.5957 0.00765 0.00219 -0.0278 0.3536 0.8498 3.250 0.6234 0.00773 0.00225 -0.0278 0.3503 0.8510 3.500 0.6511 0.00780 0.00231 -0.0279 0.3468 0.8521 3.750 0.6786 0.00789 0.00238 -0.0279 0.3425 0.8531 4.000 0.7058 0.00799 0.00246 -0.0279 0.3383 0.8542 4.250 0.7333 0.00808 0.00254 -0.0280 0.3347 0.8553 4.500 0.7608 0.00816 0.00262 -0.0280 0.3308 0.8564 4.750 0.7879 0.00826 0.00271 -0.0280 0.3267 0.8575 5.000 0.8146 0.00840 0.00281 -0.0280 0.3216 0.8586 5.250 0.8420 0.00848 0.00291 -0.0280 0.3179 0.8595 5.500 0.8689 0.00858 0.00302 -0.0280 0.3134 0.8607 5.750 0.8952 0.00871 0.00314 -0.0279 0.3085 0.8621 6.000 0.9217 0.00882 0.00326 -0.0278 0.3039 0.8635 6.250 0.9481 0.00894 0.00339 -0.0277 0.2987 0.8648 6.500 0.9738 0.00910 0.00354 -0.0275 0.2929 0.8662 6.750 1.0001 0.00922 0.00368 -0.0274 0.2873 0.8676 7.000 1.0256 0.00939 0.00384 -0.0272 0.2804 0.8690 7.250 1.0510 0.00956 0.00400 -0.0270 0.2736 0.8705 7.500 1.0761 0.00974 0.00419 -0.0267 0.2662 0.8720 7.750 1.1010 0.00994 0.00438 -0.0265 0.2586 0.8736 8.000 1.1251 0.01018 0.00459 -0.0260 0.2498 0.8751 8.500 1.1725 0.01064 0.00505 -0.0251 0.2320 0.8784 8.750 1.1949 0.01093 0.00532 -0.0244 0.2220 0.8803 9.000 1.2173 0.01120 0.00559 -0.0237 0.2120 0.8825 9.250 1.2383 0.01154 0.00591 -0.0228 0.2007 0.8850 9.500 1.2584 0.01191 0.00625 -0.0218 0.1885 0.8876 9.750 1.2772 0.01235 0.00664 -0.0206 0.1749 0.8901 10.000 1.2955 0.01277 0.00703 -0.0193 0.1633 0.8926 10.250 1.3115 0.01324 0.00748 -0.0176 0.1502 0.8957 10.500 1.3251 0.01373 0.00793 -0.0155 0.1378 0.8994 10.750 1.3359 0.01424 0.00841 -0.0128 0.1261 0.9039 11.000 1.3470 0.01475 0.00892 -0.0103 0.1166 0.9084 11.250 1.3576 0.01526 0.00944 -0.0078 0.1081 0.9141 11.500 1.3663 0.01586 0.01004 -0.0050 0.0992 0.9212 11.750 1.3741 0.01648 0.01068 -0.0022 0.0920 0.9301 12.000 1.3819 0.01714 0.01138 0.0003 0.0843 0.9431 12.250 1.3951 0.01797 0.01225 0.0014 0.0763 0.9634 12.500 1.4201 0.01904 0.01334 -0.0005 0.0683 0.9948 12.750 1.4238 0.02008 0.01439 0.0019 0.0629 1.0000 13.000 1.4287 0.02132 0.01564 0.0037 0.0573 1.0000 13.250 1.4332 0.02272 0.01706 0.0051 0.0530 1.0000 13.500 1.4367 0.02432 0.01869 0.0063 0.0482 1.0000 13.750 1.4365 0.02636 0.02075 0.0073 0.0432 1.0000 14.000 1.4420 0.02810 0.02255 0.0078 0.0412 1.0000 14.250 1.4430 0.03032 0.02482 0.0082 0.0378 1.0000 14.500 1.4421 0.03285 0.02739 0.0084 0.0349 1.0000 14.750 1.4379 0.03582 0.03040 0.0085 0.0308 1.0000 15.000 1.4359 0.03864 0.03328 0.0084 0.0290 1.0000 15.250 1.4339 0.04152 0.03623 0.0082 0.0272 1.0000 15.500 1.4282 0.04484 0.03960 0.0079 0.0252 1.0000 15.750 1.4206 0.04843 0.04326 0.0074 0.0231 1.0000 16.000 1.4198 0.05135 0.04629 0.0069 0.0235 1.0000 16.250 1.4092 0.05546 0.05044 0.0062 0.0207 1.0000 16.500 1.4004 0.05944 0.05448 0.0054 0.0190 1.0000 16.750 1.3938 0.06326 0.05838 0.0045 0.0178 1.0000 17.000 1.3860 0.06727 0.06246 0.0036 0.0167 1.0000 17.250 1.3765 0.07159 0.06683 0.0024 0.0154 1.0000 17.500 1.3720 0.07533 0.07066 0.0014 0.0152 1.0000 17.750 1.3661 0.07930 0.07471 0.0002 0.0146 1.0000 18.000 1.3569 0.08377 0.07924 -0.0012 0.0133 1.0000