XFOIL Version 6.96 Calculated polar for: EPPLER 479 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 ------ -------- --------- --------- -------- -------- -------- -18.750 -1.2559 0.08521 0.08097 -0.0175 1.0000 0.0208 -18.500 -1.2707 0.07990 0.07557 -0.0197 1.0000 0.0213 -18.250 -1.2849 0.07474 0.07033 -0.0218 1.0000 0.0218 -18.000 -1.2985 0.06977 0.06527 -0.0237 1.0000 0.0223 -17.750 -1.3117 0.06491 0.06033 -0.0256 1.0000 0.0230 -17.500 -1.3242 0.06026 0.05559 -0.0274 1.0000 0.0236 -17.250 -1.3345 0.05598 0.05122 -0.0289 1.0000 0.0242 -17.000 -1.3452 0.05176 0.04692 -0.0303 1.0000 0.0249 -16.750 -1.3550 0.04773 0.04280 -0.0316 1.0000 0.0255 -16.500 -1.3637 0.04386 0.03886 -0.0328 1.0000 0.0266 -16.250 -1.3688 0.04046 0.03538 -0.0338 1.0000 0.0276 -16.000 -1.3708 0.03744 0.03228 -0.0346 1.0000 0.0285 -15.750 -1.3732 0.03446 0.02925 -0.0353 1.0000 0.0296 -15.500 -1.3737 0.03179 0.02651 -0.0357 1.0000 0.0310 -15.250 -1.3713 0.02952 0.02418 -0.0359 1.0000 0.0323 -15.000 -1.3682 0.02745 0.02206 -0.0358 1.0000 0.0340 -14.750 -1.3656 0.02550 0.02007 -0.0354 1.0000 0.0358 -14.500 -1.3603 0.02394 0.01846 -0.0347 1.0000 0.0375 -14.250 -1.3544 0.02258 0.01706 -0.0337 1.0000 0.0395 -14.000 -1.3502 0.02126 0.01572 -0.0321 1.0000 0.0420 -13.750 -1.3424 0.02030 0.01472 -0.0305 1.0000 0.0440 -13.500 -1.3336 0.01948 0.01387 -0.0286 1.0000 0.0456 -13.250 -1.3273 0.01864 0.01302 -0.0262 1.0000 0.0486 -13.000 -1.3173 0.01804 0.01239 -0.0239 1.0000 0.0509 -12.750 -1.3080 0.01747 0.01180 -0.0212 1.0000 0.0531 -12.500 -1.2991 0.01691 0.01125 -0.0184 1.0000 0.0563 -12.250 -1.2839 0.01646 0.01078 -0.0165 1.0000 0.0589 -12.000 -1.2686 0.01594 0.01027 -0.0147 1.0000 0.0623 -11.750 -1.2514 0.01549 0.00981 -0.0131 1.0000 0.0656 -11.500 -1.2326 0.01510 0.00941 -0.0117 1.0000 0.0685 -11.250 -1.2152 0.01462 0.00896 -0.0101 1.0000 0.0731 -11.000 -1.1955 0.01426 0.00859 -0.0087 1.0000 0.0766 -10.750 -1.1764 0.01386 0.00821 -0.0073 1.0000 0.0807 -10.500 -1.1568 0.01349 0.00785 -0.0059 1.0000 0.0853 -10.250 -1.1373 0.01311 0.00749 -0.0045 1.0000 0.0911 -10.000 -1.1175 0.01274 0.00715 -0.0031 1.0000 0.0973 -9.750 -1.0971 0.01240 0.00683 -0.0018 1.0000 0.1026 -9.500 -1.0650 0.01203 0.00650 -0.0029 0.9956 0.1087 -9.250 -1.0327 0.01171 0.00618 -0.0040 0.9876 0.1140 -9.000 -0.9970 0.01135 0.00586 -0.0058 0.9751 0.1205 -8.750 -0.9499 0.01099 0.00550 -0.0099 0.9381 0.1278 -8.500 -0.9204 0.01082 0.00519 -0.0101 0.8785 0.1340 -8.250 -0.8975 0.01072 0.00496 -0.0090 0.8354 0.1392 -8.000 -0.8740 0.01056 0.00472 -0.0081 0.8025 0.1459 -7.750 -0.8492 0.01045 0.00451 -0.0074 0.7740 0.1511 -7.500 -0.8247 0.01027 0.00428 -0.0068 0.7477 0.1585 -7.250 -0.7991 0.01014 0.00409 -0.0062 0.7250 0.1651 -7.000 -0.7737 0.00996 0.00388 -0.0057 0.7035 0.1728 -6.750 -0.7475 0.00984 0.00371 -0.0053 0.6839 0.1794 -6.500 -0.7215 0.00969 0.00352 -0.0048 0.6640 0.1865 -6.250 -0.6950 0.00958 0.00337 -0.0045 0.6455 0.1936 -6.000 -0.6685 0.00944 0.00320 -0.0041 0.6292 0.2009 -5.750 -0.6416 0.00934 0.00306 -0.0038 0.6126 0.2083 -5.500 -0.6148 0.00922 0.00292 -0.0035 0.5959 0.2158 -5.250 -0.5877 0.00913 0.00279 -0.0032 0.5804 0.2232 -5.000 -0.5605 0.00903 0.00267 -0.0030 0.5661 0.2303 -4.750 -0.5331 0.00894 0.00256 -0.0027 0.5514 0.2382 -4.500 -0.5056 0.00887 0.00245 -0.0025 0.5370 0.2444 -4.250 -0.4781 0.00879 0.00236 -0.0023 0.5235 0.2524 -4.000 -0.4503 0.00875 0.00227 -0.0021 0.5113 0.2584 -3.750 -0.4226 0.00867 0.00219 -0.0019 0.4987 0.2656 -3.500 -0.3946 0.00863 0.00212 -0.0018 0.4870 0.2721 -3.250 -0.3668 0.00858 0.00204 -0.0016 0.4748 0.2782 -3.000 -0.3388 0.00853 0.00198 -0.0015 0.4641 0.2849 -2.750 -0.3106 0.00851 0.00193 -0.0013 0.4543 0.2904 -2.250 -0.2544 0.00844 0.00183 -0.0010 0.4331 0.3034 -2.000 -0.2263 0.00842 0.00178 -0.0009 0.4238 0.3086 -1.750 -0.1981 0.00838 0.00175 -0.0008 0.4147 0.3152 -1.500 -0.1698 0.00838 0.00172 -0.0007 0.4055 0.3210 -1.250 -0.1415 0.00836 0.00169 -0.0006 0.3969 0.3264 -1.000 -0.1133 0.00835 0.00167 -0.0004 0.3887 0.3331 -0.750 -0.0848 0.00835 0.00165 -0.0003 0.3805 0.3389 -0.500 -0.0567 0.00835 0.00164 -0.0002 0.3726 0.3450 -0.250 -0.0283 0.00833 0.00163 -0.0001 0.3654 0.3520 0.000 0.0000 0.00835 0.00163 0.0000 0.3580 0.3582 0.250 0.0283 0.00833 0.00163 0.0001 0.3520 0.3655 0.500 0.0567 0.00835 0.00164 0.0002 0.3449 0.3726 0.750 0.0848 0.00835 0.00165 0.0003 0.3389 0.3805 1.000 0.1133 0.00835 0.00167 0.0004 0.3330 0.3887 1.250 0.1415 0.00836 0.00169 0.0006 0.3264 0.3968 1.500 0.1698 0.00838 0.00172 0.0007 0.3210 0.4055 1.750 0.1981 0.00838 0.00175 0.0008 0.3151 0.4147 2.000 0.2263 0.00842 0.00178 0.0009 0.3086 0.4238 2.250 0.2544 0.00844 0.00183 0.0010 0.3032 0.4330 2.500 0.2827 0.00847 0.00187 0.0012 0.2972 0.4431 2.750 0.3106 0.00851 0.00193 0.0013 0.2904 0.4542 3.000 0.3388 0.00853 0.00198 0.0015 0.2851 0.4641 3.250 0.3668 0.00858 0.00204 0.0016 0.2782 0.4747 3.500 0.3946 0.00863 0.00212 0.0018 0.2722 0.4867 3.750 0.4226 0.00867 0.00219 0.0019 0.2658 0.4989 4.000 0.4503 0.00875 0.00227 0.0021 0.2585 0.5113 4.250 0.4781 0.00879 0.00236 0.0023 0.2521 0.5235 4.500 0.5056 0.00887 0.00245 0.0025 0.2444 0.5371 4.750 0.5331 0.00894 0.00256 0.0027 0.2381 0.5517 5.000 0.5605 0.00903 0.00267 0.0030 0.2301 0.5662 5.250 0.5877 0.00913 0.00279 0.0032 0.2231 0.5805 5.500 0.6148 0.00922 0.00292 0.0035 0.2160 0.5961 5.750 0.6416 0.00934 0.00306 0.0038 0.2081 0.6128 6.000 0.6685 0.00944 0.00320 0.0041 0.2010 0.6294 6.250 0.6950 0.00958 0.00337 0.0045 0.1936 0.6454 6.500 0.7215 0.00969 0.00352 0.0048 0.1865 0.6639 6.750 0.7475 0.00985 0.00371 0.0053 0.1794 0.6833 7.000 0.7738 0.00996 0.00388 0.0057 0.1729 0.7033 7.250 0.7991 0.01014 0.00409 0.0062 0.1651 0.7250 7.500 0.8247 0.01026 0.00428 0.0068 0.1587 0.7483 7.750 0.8493 0.01045 0.00451 0.0074 0.1513 0.7739 8.000 0.8741 0.01056 0.00472 0.0081 0.1459 0.8028 8.250 0.8977 0.01071 0.00495 0.0090 0.1396 0.8354 8.500 0.9205 0.01082 0.00519 0.0101 0.1340 0.8777 8.750 0.9501 0.01099 0.00550 0.0099 0.1278 0.9382 9.000 0.9970 0.01135 0.00586 0.0058 0.1207 0.9751 9.250 1.0327 0.01171 0.00618 0.0040 0.1139 0.9876 9.500 1.0653 0.01204 0.00650 0.0028 0.1086 0.9958 9.750 1.0971 0.01240 0.00683 0.0018 0.1026 1.0000 10.000 1.1175 0.01274 0.00715 0.0031 0.0973 1.0000 10.250 1.1372 0.01312 0.00750 0.0045 0.0907 1.0000 10.500 1.1569 0.01349 0.00785 0.0059 0.0854 1.0000 10.750 1.1764 0.01387 0.00821 0.0073 0.0806 1.0000 11.000 1.1956 0.01426 0.00859 0.0087 0.0767 1.0000 11.250 1.2152 0.01463 0.00896 0.0101 0.0729 1.0000 11.500 1.2330 0.01509 0.00940 0.0116 0.0688 1.0000 11.750 1.2515 0.01549 0.00981 0.0131 0.0655 1.0000 12.000 1.2688 0.01594 0.01027 0.0146 0.0623 1.0000 12.250 1.2841 0.01646 0.01078 0.0165 0.0587 1.0000 12.500 1.2995 0.01691 0.01125 0.0183 0.0562 1.0000 12.750 1.3088 0.01745 0.01179 0.0211 0.0533 1.0000 13.000 1.3176 0.01804 0.01239 0.0238 0.0506 1.0000 13.250 1.3271 0.01867 0.01304 0.0262 0.0481 1.0000 13.500 1.3345 0.01947 0.01386 0.0285 0.0456 1.0000 13.750 1.3429 0.02031 0.01472 0.0304 0.0437 1.0000 14.000 1.3505 0.02129 0.01574 0.0321 0.0415 1.0000 14.250 1.3544 0.02262 0.01709 0.0336 0.0391 1.0000 14.500 1.3618 0.02389 0.01841 0.0346 0.0378 1.0000 14.750 1.3670 0.02546 0.02002 0.0353 0.0358 1.0000 15.000 1.3702 0.02736 0.02197 0.0357 0.0341 1.0000 15.250 1.3729 0.02947 0.02413 0.0357 0.0323 1.0000 15.500 1.3755 0.03173 0.02645 0.0355 0.0310 1.0000 15.750 1.3749 0.03444 0.02922 0.0350 0.0295 1.0000 16.000 1.3729 0.03738 0.03222 0.0343 0.0285 1.0000 16.250 1.3708 0.04043 0.03535 0.0335 0.0274 1.0000 16.500 1.3663 0.04377 0.03876 0.0325 0.0265 1.0000 16.750 1.3587 0.04754 0.04261 0.0313 0.0257 1.0000 17.250 1.3377 0.05586 0.05110 0.0286 0.0241 1.0000 17.500 1.3273 0.06017 0.05549 0.0270 0.0234 1.0000 17.750 1.3122 0.06518 0.06058 0.0251 0.0223 1.0000 18.000 1.3015 0.06972 0.06522 0.0234 0.0222 1.0000 18.250 1.2880 0.07468 0.07026 0.0214 0.0217 1.0000 18.500 1.2737 0.07985 0.07552 0.0193 0.0212 1.0000 18.750 1.2592 0.08514 0.08089 0.0171 0.0206 1.0000