XFOIL Version 6.96 Calculated polar for: EPPLER 327 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3592 0.08687 0.08479 -0.0231 1.0000 0.0075 -10.000 -0.3669 0.08122 0.07916 -0.0252 1.0000 0.0073 -9.750 -0.3789 0.07475 0.07271 -0.0279 1.0000 0.0071 -9.500 -0.3942 0.06780 0.06578 -0.0318 1.0000 0.0071 -9.000 -0.5540 0.06100 0.05861 -0.0333 1.0000 0.0065 -8.500 -0.5786 0.05273 0.05007 -0.0275 0.9887 0.0063 -8.250 -0.5524 0.04505 0.04197 -0.0339 0.9083 0.0062 -8.000 -0.5571 0.03762 0.03388 -0.0310 0.8411 0.0064 -7.750 -0.5526 0.03547 0.03138 -0.0280 0.8005 0.0066 -7.500 -0.5562 0.02983 0.02510 -0.0231 0.7754 0.0065 -7.000 -0.5315 0.02490 0.01926 -0.0178 0.7307 0.0063 -6.750 -0.5152 0.02289 0.01688 -0.0158 0.7114 0.0062 -6.500 -0.4958 0.02130 0.01496 -0.0143 0.6931 0.0062 -6.250 -0.4743 0.01986 0.01321 -0.0131 0.6767 0.0062 -6.000 -0.4513 0.01868 0.01178 -0.0122 0.6609 0.0062 -5.750 -0.4273 0.01762 0.01048 -0.0114 0.6457 0.0062 -5.500 -0.4030 0.01672 0.00940 -0.0106 0.6322 0.0062 -5.250 -0.3788 0.01602 0.00855 -0.0099 0.6194 0.0062 -5.000 -0.3548 0.01536 0.00776 -0.0091 0.6064 0.0063 -4.750 -0.3314 0.01473 0.00701 -0.0082 0.5936 0.0063 -4.500 -0.3090 0.01405 0.00624 -0.0072 0.5817 0.0065 -4.250 -0.2859 0.01359 0.00571 -0.0062 0.5713 0.0066 -4.000 -0.2629 0.01320 0.00524 -0.0053 0.5603 0.0068 -3.750 -0.2394 0.01284 0.00482 -0.0044 0.5495 0.0072 -3.500 -0.2156 0.01255 0.00446 -0.0036 0.5393 0.0074 -3.250 -0.1917 0.01229 0.00412 -0.0028 0.5294 0.0078 -3.000 -0.1673 0.01205 0.00382 -0.0021 0.5204 0.0083 -2.750 -0.1434 0.01181 0.00351 -0.0012 0.5113 0.0097 -2.500 -0.1188 0.01161 0.00326 -0.0006 0.5020 0.0115 -2.250 -0.0946 0.01140 0.00304 0.0002 0.4936 0.0179 -2.000 -0.0708 0.01115 0.00286 0.0009 0.4855 0.0381 -1.750 -0.0475 0.01088 0.00271 0.0018 0.4781 0.0755 -1.500 -0.0270 0.01040 0.00255 0.0030 0.4702 0.1682 -1.000 -0.0226 0.00790 0.00242 0.0130 0.4587 0.8096 -0.750 0.0035 0.00804 0.00249 0.0136 0.4517 0.8258 -0.500 0.0296 0.00818 0.00256 0.0143 0.4453 0.8389 -0.250 0.0551 0.00838 0.00270 0.0151 0.4381 0.8517 0.000 0.0818 0.00857 0.00285 0.0157 0.4316 0.8595 0.250 0.1078 0.00870 0.00292 0.0163 0.4255 0.8669 0.500 0.1349 0.00876 0.00289 0.0164 0.4195 0.8693 0.750 0.1629 0.00878 0.00286 0.0164 0.4135 0.8703 1.000 0.1906 0.00883 0.00285 0.0164 0.4073 0.8714 1.250 0.2181 0.00888 0.00283 0.0164 0.4021 0.8724 1.500 0.2460 0.00892 0.00283 0.0163 0.3968 0.8734 1.750 0.2736 0.00897 0.00283 0.0163 0.3911 0.8746 2.000 0.3009 0.00904 0.00285 0.0163 0.3860 0.8760 2.250 0.3287 0.00908 0.00287 0.0163 0.3811 0.8772 2.500 0.3561 0.00915 0.00289 0.0162 0.3757 0.8783 2.750 0.3834 0.00922 0.00292 0.0162 0.3710 0.8795 3.000 0.4111 0.00927 0.00296 0.0161 0.3663 0.8807 3.250 0.4385 0.00934 0.00300 0.0161 0.3613 0.8819 3.500 0.4655 0.00944 0.00306 0.0161 0.3565 0.8833 3.750 0.4931 0.00950 0.00312 0.0160 0.3521 0.8845 4.000 0.5204 0.00957 0.00319 0.0160 0.3472 0.8855 4.250 0.5472 0.00968 0.00327 0.0160 0.3424 0.8865 4.500 0.5744 0.00976 0.00337 0.0160 0.3381 0.8875 4.750 0.6015 0.00985 0.00347 0.0160 0.3331 0.8886 5.000 0.6281 0.00997 0.00357 0.0161 0.3282 0.8898 5.250 0.6549 0.01007 0.00370 0.0161 0.3236 0.8911 5.500 0.6818 0.01017 0.00382 0.0161 0.3185 0.8924 5.750 0.7081 0.01030 0.00394 0.0162 0.3131 0.8938 6.000 0.7347 0.01042 0.00409 0.0162 0.3081 0.8954 6.250 0.7612 0.01054 0.00423 0.0163 0.3024 0.8971 6.750 0.8135 0.01083 0.00454 0.0164 0.2906 0.9000 7.000 0.8390 0.01098 0.00472 0.0166 0.2842 0.9013 7.250 0.8644 0.01114 0.00490 0.0168 0.2781 0.9027 7.500 0.8895 0.01131 0.00510 0.0171 0.2703 0.9042 7.750 0.9144 0.01149 0.00531 0.0174 0.2636 0.9059 8.000 0.9389 0.01170 0.00553 0.0177 0.2551 0.9078 8.250 0.9633 0.01191 0.00578 0.0180 0.2468 0.9097 8.500 0.9867 0.01217 0.00604 0.0185 0.2379 0.9118 8.750 1.0104 0.01243 0.00631 0.0189 0.2274 0.9140 9.000 1.0331 0.01270 0.00661 0.0194 0.2176 0.9162 9.250 1.0543 0.01303 0.00695 0.0203 0.2063 0.9187 9.500 1.0746 0.01339 0.00731 0.0212 0.1949 0.9215 9.750 1.0941 0.01380 0.00771 0.0222 0.1820 0.9247 10.000 1.1126 0.01426 0.00816 0.0234 0.1686 0.9281 10.500 1.1448 0.01529 0.00917 0.0264 0.1416 0.9360 10.750 1.1581 0.01588 0.00974 0.0283 0.1280 0.9416 11.000 1.1684 0.01648 0.01035 0.0307 0.1156 0.9485 11.250 1.1793 0.01716 0.01103 0.0328 0.1044 0.9577 11.500 1.1954 0.01797 0.01185 0.0335 0.0933 0.9675 11.750 1.2155 0.01887 0.01278 0.0331 0.0834 0.9786 12.000 1.2362 0.01990 0.01384 0.0322 0.0746 1.0000 12.250 1.2396 0.02097 0.01492 0.0344 0.0683 1.0000 12.500 1.2445 0.02211 0.01609 0.0361 0.0628 1.0000 12.750 1.2464 0.02360 0.01761 0.0375 0.0573 1.0000 13.000 1.2492 0.02522 0.01927 0.0386 0.0527 1.0000 13.250 1.2498 0.02718 0.02127 0.0393 0.0485 1.0000 13.500 1.2509 0.02927 0.02342 0.0396 0.0447 1.0000 13.750 1.2486 0.03182 0.02602 0.0398 0.0412 1.0000 14.000 1.2489 0.03423 0.02851 0.0397 0.0385 1.0000 14.250 1.2457 0.03708 0.03143 0.0395 0.0358 1.0000 14.500 1.2409 0.04019 0.03461 0.0391 0.0335 1.0000 14.750 1.2378 0.04318 0.03768 0.0386 0.0316 1.0000 15.000 1.2314 0.04658 0.04115 0.0379 0.0295 1.0000 15.500 1.2177 0.05371 0.04843 0.0363 0.0261 1.0000 15.750 1.2115 0.05735 0.05216 0.0353 0.0252 1.0000 16.000 1.2036 0.06132 0.05620 0.0341 0.0237 1.0000 16.500 1.1900 0.06930 0.06434 0.0315 0.0215 1.0000 16.750 1.1835 0.07336 0.06849 0.0300 0.0203 1.0000 17.000 1.1763 0.07761 0.07282 0.0284 0.0194 1.0000 17.250 1.1681 0.08211 0.07738 0.0266 0.0185 1.0000 17.500 1.1619 0.08641 0.08176 0.0249 0.0177 1.0000 17.750 1.1564 0.09065 0.08609 0.0231 0.0166 1.0000 18.000 1.1474 0.09548 0.09096 0.0210 0.0149 1.0000 18.250 1.1436 0.09966 0.09526 0.0192 0.0153 1.0000