XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0406 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 -0.7385 0.09284 0.09128 0.0142 1.0000 0.0044 -9.750 -0.7468 0.08590 0.08437 0.0097 1.0000 0.0044 -9.250 -0.8595 0.02997 0.02722 -0.0282 1.0000 0.0044 -9.000 -0.8396 0.02728 0.02426 -0.0289 1.0000 0.0045 -8.750 -0.8180 0.02489 0.02161 -0.0294 1.0000 0.0047 -8.500 -0.7949 0.02288 0.01933 -0.0299 1.0000 0.0049 -8.250 -0.7707 0.02096 0.01715 -0.0303 1.0000 0.0051 -8.000 -0.7457 0.01930 0.01524 -0.0306 1.0000 0.0053 -7.750 -0.7199 0.01777 0.01349 -0.0310 1.0000 0.0054 -7.500 -0.6936 0.01644 0.01195 -0.0313 1.0000 0.0056 -7.250 -0.6668 0.01519 0.01051 -0.0315 1.0000 0.0057 -7.000 -0.6397 0.01411 0.00927 -0.0318 1.0000 0.0058 -6.750 -0.6123 0.01319 0.00820 -0.0321 1.0000 0.0060 -6.500 -0.5846 0.01248 0.00737 -0.0323 1.0000 0.0062 -6.250 -0.5567 0.01175 0.00654 -0.0326 1.0000 0.0063 -6.000 -0.5286 0.01099 0.00567 -0.0329 1.0000 0.0064 -5.750 -0.5002 0.01035 0.00494 -0.0332 1.0000 0.0064 -5.500 -0.4716 0.00981 0.00432 -0.0336 1.0000 0.0065 -5.250 -0.4430 0.00936 0.00378 -0.0339 1.0000 0.0066 -5.000 -0.4144 0.00898 0.00334 -0.0342 1.0000 0.0067 -4.750 -0.3859 0.00866 0.00298 -0.0345 1.0000 0.0069 -4.500 -0.3571 0.00830 0.00256 -0.0348 1.0000 0.0075 -4.250 -0.3284 0.00803 0.00226 -0.0350 1.0000 0.0089 -4.000 -0.2999 0.00780 0.00202 -0.0352 1.0000 0.0104 -3.750 -0.2715 0.00757 0.00183 -0.0355 1.0000 0.0166 -3.500 -0.2432 0.00736 0.00168 -0.0357 1.0000 0.0262 -3.250 -0.2150 0.00719 0.00155 -0.0358 1.0000 0.0335 -3.000 -0.1870 0.00701 0.00142 -0.0360 1.0000 0.0465 -2.750 -0.1592 0.00683 0.00133 -0.0361 1.0000 0.0625 -2.500 -0.1316 0.00663 0.00123 -0.0362 1.0000 0.0884 -2.250 -0.1018 0.00632 0.00113 -0.0368 0.9988 0.1429 -2.000 -0.0662 0.00593 0.00101 -0.0389 0.9935 0.2263 -1.750 -0.0291 0.00553 0.00090 -0.0413 0.9802 0.3156 -1.500 0.0050 0.00500 0.00083 -0.0430 0.9498 0.4654 -1.250 0.0317 0.00478 0.00083 -0.0427 0.9158 0.5545 -1.000 0.0580 0.00475 0.00082 -0.0422 0.8840 0.5997 -0.750 0.0849 0.00479 0.00082 -0.0419 0.8489 0.6225 -0.500 0.1112 0.00498 0.00082 -0.0414 0.7783 0.6490 -0.250 0.1385 0.00521 0.00084 -0.0413 0.7053 0.6682 0.000 0.1658 0.00562 0.00089 -0.0413 0.5872 0.6865 0.250 0.1927 0.00636 0.00101 -0.0415 0.3950 0.7087 0.500 0.2202 0.00694 0.00114 -0.0418 0.2450 0.7283 0.750 0.2478 0.00745 0.00127 -0.0420 0.1269 0.7422 1.000 0.2759 0.00768 0.00137 -0.0422 0.0838 0.7538 1.250 0.3041 0.00785 0.00149 -0.0423 0.0584 0.7642 1.500 0.3323 0.00799 0.00160 -0.0424 0.0448 0.7735 1.750 0.3605 0.00814 0.00172 -0.0424 0.0345 0.7818 2.000 0.3886 0.00831 0.00186 -0.0425 0.0239 0.7902 2.250 0.4165 0.00853 0.00205 -0.0425 0.0122 0.7975 2.500 0.4446 0.00870 0.00224 -0.0425 0.0093 0.8050 2.750 0.4726 0.00887 0.00246 -0.0425 0.0090 0.8127 3.250 0.5281 0.00928 0.00298 -0.0424 0.0082 0.8324 3.500 0.5557 0.00952 0.00330 -0.0423 0.0079 0.8418 3.750 0.5831 0.00980 0.00365 -0.0422 0.0077 0.8511 4.000 0.6103 0.01010 0.00403 -0.0421 0.0074 0.8604 4.250 0.6373 0.01044 0.00444 -0.0419 0.0072 0.8698 4.500 0.6640 0.01081 0.00489 -0.0416 0.0069 0.8806 4.750 0.6903 0.01122 0.00541 -0.0413 0.0066 0.8924 5.000 0.7159 0.01178 0.00608 -0.0408 0.0062 0.9045 5.250 0.7399 0.01302 0.00754 -0.0401 0.0056 0.9174 5.500 0.7636 0.01401 0.00872 -0.0392 0.0055 0.9313 5.750 0.7858 0.01470 0.00958 -0.0379 0.0054 0.9547 6.000 0.8103 0.01565 0.01071 -0.0373 0.0053 1.0000 6.250 0.8358 0.01693 0.01221 -0.0370 0.0053 1.0000 6.500 0.8614 0.01801 0.01346 -0.0367 0.0051 1.0000 6.750 0.8865 0.01916 0.01480 -0.0365 0.0050 1.0000 7.000 0.9102 0.02084 0.01672 -0.0360 0.0048 1.0000 7.250 0.9318 0.02325 0.01947 -0.0354 0.0047 1.0000 7.500 0.9502 0.02670 0.02336 -0.0344 0.0046 1.0000 7.750 0.9180 0.05185 0.04995 -0.0314 0.0043 1.0000 8.000 0.9121 0.06273 0.06114 -0.0332 0.0041 1.0000 8.250 0.9052 0.07216 0.07075 -0.0369 0.0040 1.0000 8.500 0.8963 0.08103 0.07973 -0.0428 0.0040 1.0000 8.750 0.8805 0.08946 0.08817 -0.0516 0.0040 1.0000