XFOIL Version 6.96 Calculated polar for: GOE 433 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 ------ -------- --------- --------- -------- -------- -------- -18.250 -0.9891 0.08637 0.08326 -0.0638 1.0000 0.0405 -18.000 -1.0118 0.07961 0.07641 -0.0681 1.0000 0.0410 -17.750 -1.0348 0.07292 0.06962 -0.0724 1.0000 0.0414 -17.500 -1.0579 0.06636 0.06296 -0.0767 1.0000 0.0418 -17.250 -1.0783 0.06029 0.05679 -0.0807 1.0000 0.0422 -17.000 -1.0972 0.05458 0.05097 -0.0846 1.0000 0.0425 -16.750 -1.1150 0.04905 0.04532 -0.0885 1.0000 0.0428 -16.500 -1.1275 0.04424 0.04042 -0.0919 1.0000 0.0431 -16.250 -1.1422 0.03917 0.03526 -0.0958 1.0000 0.0435 -16.000 -1.1446 0.03477 0.03076 -0.1006 0.9796 0.0440 -15.750 -1.1440 0.03109 0.02699 -0.1043 0.9570 0.0446 -15.500 -1.1419 0.02797 0.02374 -0.1072 0.9364 0.0452 -15.250 -1.1278 0.02524 0.02089 -0.1113 0.9192 0.0460 -15.000 -1.1065 0.02285 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0.5182 0.1844 -0.500 0.5618 0.00855 0.00212 -0.1381 0.5056 0.2152 -0.250 0.5914 0.00851 0.00214 -0.1384 0.4984 0.2339 0.000 0.6205 0.00854 0.00216 -0.1385 0.4897 0.2497 0.250 0.6493 0.00858 0.00220 -0.1386 0.4752 0.2680 0.500 0.6779 0.00865 0.00225 -0.1386 0.4606 0.2834 0.750 0.7066 0.00873 0.00231 -0.1387 0.4507 0.2928 1.000 0.7353 0.00881 0.00237 -0.1388 0.4414 0.3030 1.250 0.7638 0.00891 0.00245 -0.1388 0.4305 0.3121 1.500 0.7917 0.00906 0.00255 -0.1387 0.4169 0.3234 1.750 0.8198 0.00917 0.00265 -0.1387 0.4047 0.3355 2.000 0.8481 0.00927 0.00275 -0.1387 0.3954 0.3526 2.250 0.8762 0.00937 0.00287 -0.1387 0.3854 0.3741 2.500 0.9043 0.00948 0.00299 -0.1387 0.3758 0.3966 2.750 0.9319 0.00963 0.00314 -0.1386 0.3649 0.4184 3.000 0.9598 0.00977 0.00328 -0.1386 0.3543 0.4334 3.250 0.9868 0.00998 0.00344 -0.1384 0.3419 0.4479 3.500 1.0139 0.01017 0.00361 -0.1382 0.3299 0.4601 3.750 1.0409 0.01038 0.00377 -0.1380 0.3176 0.4679 4.000 1.0667 0.01067 0.00399 -0.1376 0.3005 0.4756 4.250 1.0915 0.01103 0.00424 -0.1371 0.2795 0.4827 4.500 1.1151 0.01148 0.00456 -0.1364 0.2546 0.4892 4.750 1.1371 0.01202 0.00495 -0.1355 0.2251 0.4968 5.000 1.1515 0.01310 0.00569 -0.1335 0.1669 0.5025 5.500 1.1958 0.01401 0.00644 -0.1318 0.1367 0.5106 5.750 1.2179 0.01443 0.00680 -0.1308 0.1252 0.5150 6.000 1.2394 0.01487 0.00718 -0.1298 0.1136 0.5198 6.250 1.2596 0.01536 0.00759 -0.1287 0.1011 0.5244 6.750 1.2827 0.01694 0.00896 -0.1236 0.0537 0.5339 7.000 1.3013 0.01741 0.00944 -0.1222 0.0515 0.5398 7.250 1.3202 0.01787 0.00991 -0.1209 0.0499 0.5457 7.500 1.3393 0.01832 0.01040 -0.1197 0.0491 0.5536 7.750 1.3578 0.01881 0.01093 -0.1185 0.0484 0.5610 8.000 1.3756 0.01936 0.01150 -0.1172 0.0478 0.5680 8.250 1.3929 0.01994 0.01213 -0.1160 0.0472 0.5779 8.500 1.4096 0.02058 0.01281 -0.1147 0.0466 0.5876 8.750 1.4256 0.02128 0.01356 -0.1134 0.0461 0.5977 9.000 1.4412 0.02204 0.01436 -0.1121 0.0456 0.6088 9.500 1.4707 0.02374 0.01623 -0.1097 0.0447 0.6502 9.750 1.4863 0.02456 0.01720 -0.1088 0.0445 0.7059 10.000 1.4976 0.02502 0.01819 -0.1069 0.0444 1.0000 10.250 1.5117 0.02604 0.01924 -0.1059 0.0442 1.0000 10.500 1.5249 0.02716 0.02038 -0.1048 0.0440 1.0000 10.750 1.5374 0.02833 0.02159 -0.1037 0.0438 1.0000 11.000 1.5495 0.02957 0.02287 -0.1027 0.0436 1.0000 11.250 1.5606 0.03092 0.02425 -0.1017 0.0434 1.0000 11.500 1.5710 0.03234 0.02571 -0.1006 0.0432 1.0000 11.750 1.5808 0.03383 0.02725 -0.0996 0.0430 1.0000 12.000 1.5895 0.03546 0.02892 -0.0986 0.0428 1.0000 12.250 1.5977 0.03718 0.03068 -0.0977 0.0427 1.0000 12.500 1.6051 0.03898 0.03252 -0.0968 0.0425 1.0000 12.750 1.6120 0.04089 0.03449 -0.0959 0.0423 1.0000 13.000 1.6182 0.04294 0.03659 -0.0952 0.0422 1.0000 13.250 1.6238 0.04510 0.03880 -0.0945 0.0420 1.0000 13.500 1.6288 0.04734 0.04110 -0.0938 0.0419 1.0000 13.750 1.6335 0.04964 0.04345 -0.0932 0.0416 1.0000 14.000 1.6372 0.05210 0.04597 -0.0927 0.0414 1.0000 14.250 1.6402 0.05466 0.04858 -0.0922 0.0411 1.0000 14.500 1.6430 0.05724 0.05121 -0.0917 0.0408 1.0000 14.750 1.6434 0.06014 0.05416 -0.0913 0.0405 1.0000 15.000 1.6435 0.06310 0.05718 -0.0909 0.0402 1.0000 15.250 1.6422 0.06625 0.06039 -0.0906 0.0399 1.0000 15.500 1.6386 0.06972 0.06394 -0.0904 0.0396 1.0000 15.750 1.6416 0.07239 0.06666 -0.0901 0.0395 1.0000 16.000 1.6419 0.07545 0.06979 -0.0900 0.0394 1.0000 16.250 1.6436 0.07835 0.07275 -0.0899 0.0393 1.0000 16.500 1.6437 0.08150 0.07596 -0.0899 0.0391 1.0000 16.750 1.6440 0.08460 0.07913 -0.0899 0.0390 1.0000 17.000 1.6435 0.08784 0.08244 -0.0900 0.0388 1.0000 17.250 1.6423 0.09122 0.08589 -0.0902 0.0387 1.0000 17.500 1.6416 0.09452 0.08925 -0.0905 0.0385 1.0000 17.750 1.6394 0.09809 0.09290 -0.0908 0.0384 1.0000 18.000 1.6392 0.10134 0.09621 -0.0912 0.0382 1.0000