GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 200,000 Max Cl/Cd: 89.01 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe427-il-200000.txt Download as CSV file: xf-goe427-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 427 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3420 0.09533 0.09193 -0.0213 1.0000 0.0241
-7.500 -0.3468 0.09366 0.09032 -0.0196 1.0000 0.0244
-7.250 -0.3527 0.09203 0.08875 -0.0177 1.0000 0.0247
-7.000 -0.3546 0.08995 0.08673 -0.0170 1.0000 0.0252
-6.750 -0.3555 0.08786 0.08469 -0.0165 1.0000 0.0256
-6.500 -0.3555 0.08574 0.08261 -0.0162 1.0000 0.0260
-6.250 -0.3545 0.08352 0.08042 -0.0163 1.0000 0.0267
-6.000 -0.3520 0.08125 0.07819 -0.0167 1.0000 0.0273
-5.750 -0.3474 0.07890 0.07586 -0.0175 1.0000 0.0282
-5.500 -0.3395 0.07656 0.07353 -0.0192 1.0000 0.0290
-5.250 -0.3080 0.07394 0.07085 -0.0273 0.9985 0.0303
-5.000 -0.2501 0.06979 0.06653 -0.0404 0.9940 0.0310
-4.750 -0.2072 0.06529 0.06191 -0.0483 0.9891 0.0311
-4.500 -0.1859 0.05778 0.05441 -0.0526 0.9852 0.0324
-4.250 -0.1595 0.05415 0.05075 -0.0552 0.9809 0.0346
-4.000 -0.1220 0.05068 0.04718 -0.0606 0.9754 0.0391
-3.750 -0.0510 0.04751 0.04360 -0.0720 0.9720 0.0438
-3.500 -0.0158 0.04136 0.03734 -0.0774 0.9694 0.0454
-2.500 0.1281 0.02991 0.02518 -0.0899 0.9497 0.0742
-2.250 0.1675 0.02758 0.02262 -0.0929 0.9458 0.0874
-2.000 0.2083 0.02547 0.02031 -0.0961 0.9431 0.1019
-1.500 0.2874 0.01786 0.01113 -0.0980 0.9339 0.0602
-1.250 0.3280 0.01645 0.00948 -0.1003 0.9307 0.0634
-1.000 0.3720 0.01520 0.00799 -0.1030 0.9285 0.0669
-0.750 0.4030 0.01433 0.00699 -0.1032 0.9195 0.0691
-0.500 0.4455 0.01335 0.00600 -0.1057 0.9157 0.0754
-0.250 0.4763 0.01272 0.00539 -0.1059 0.9061 0.0799
0.000 0.5151 0.01202 0.00475 -0.1076 0.9011 0.0899
0.250 0.5435 0.01154 0.00437 -0.1074 0.8903 0.1159
0.500 0.5883 0.00933 0.00414 -0.1110 0.8840 1.0000
0.750 0.6209 0.00916 0.00382 -0.1115 0.8738 1.0000
1.000 0.6499 0.00907 0.00362 -0.1112 0.8605 1.0000
1.250 0.6790 0.00900 0.00347 -0.1110 0.8463 1.0000
1.500 0.7057 0.00897 0.00337 -0.1103 0.8272 1.0000
1.750 0.7330 0.00892 0.00318 -0.1095 0.8022 1.0000
2.000 0.7585 0.00898 0.00309 -0.1085 0.7747 1.0000
2.250 0.7836 0.00910 0.00309 -0.1075 0.7490 1.0000
2.500 0.8079 0.00925 0.00318 -0.1065 0.7227 1.0000
2.750 0.8319 0.00943 0.00326 -0.1054 0.6952 1.0000
3.000 0.8554 0.00964 0.00336 -0.1043 0.6664 1.0000
3.250 0.8785 0.00987 0.00348 -0.1031 0.6354 1.0000
3.500 0.9005 0.01014 0.00361 -0.1017 0.5985 1.0000
3.750 0.9217 0.01052 0.00382 -0.1002 0.5597 1.0000
4.000 0.9430 0.01095 0.00407 -0.0988 0.5256 1.0000
4.250 0.9650 0.01134 0.00438 -0.0976 0.4954 1.0000
4.500 0.9871 0.01169 0.00469 -0.0964 0.4624 1.0000
4.750 1.0071 0.01214 0.00500 -0.0948 0.4081 1.0000
5.000 1.0214 0.01310 0.00549 -0.0924 0.3059 1.0000
5.250 1.0243 0.01570 0.00674 -0.0888 0.0879 1.0000
5.500 1.0427 0.01673 0.00767 -0.0871 0.0632 1.0000
5.750 1.0623 0.01756 0.00855 -0.0856 0.0541 1.0000
6.000 1.0784 0.01875 0.00978 -0.0836 0.0479 1.0000
6.250 1.0954 0.01983 0.01098 -0.0816 0.0447 1.0000
6.500 1.1107 0.02113 0.01235 -0.0796 0.0399 1.0000
6.750 1.1230 0.02363 0.01486 -0.0770 0.0368 1.0000
7.000 1.1446 0.02527 0.01661 -0.0757 0.0353 1.0000
7.250 1.1676 0.02701 0.01851 -0.0746 0.0331 1.0000
7.500 1.1901 0.02885 0.02049 -0.0737 0.0302 1.0000
7.750 1.2147 0.03143 0.02328 -0.0729 0.0293 1.0000
8.000 1.2382 0.03466 0.02690 -0.0716 0.0299 1.0000
8.250 1.2585 0.03940 0.03223 -0.0695 0.0333 1.0000
15.750 0.8650 0.19534 0.19250 -0.0948 0.0363 1.0000
16.000 0.8632 0.19971 0.19687 -0.0978 0.0360 1.0000
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Polar data table (+)
Polar graphs
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