GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 685 AIRFOIL (goe685-il) Reynolds number: 500,000 Max Cl/Cd: 100.56 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe685-il-500000.txt Download as CSV file: xf-goe685-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 685 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7505 0.07097 0.06766 -0.0728 1.0000 0.0315
-14.250 -0.7807 0.06350 0.06006 -0.0782 1.0000 0.0316
-14.000 -0.8045 0.05712 0.05355 -0.0829 1.0000 0.0315
-13.750 -0.8211 0.05212 0.04848 -0.0861 1.0000 0.0318
-13.500 -0.8322 0.04803 0.04433 -0.0885 1.0000 0.0320
-13.250 -0.8491 0.04310 0.03930 -0.0920 1.0000 0.0321
-13.000 -0.8767 0.03790 0.03396 -0.0962 1.0000 0.0320
-12.750 -0.9009 0.03607 0.03205 -0.0924 1.0000 0.0321
-12.500 -0.9128 0.03459 0.03051 -0.0891 1.0000 0.0323
-12.250 -0.9170 0.03332 0.02919 -0.0863 1.0000 0.0326
-12.000 -0.8927 0.03158 0.02735 -0.0888 0.9977 0.0332
-11.750 -0.8651 0.02984 0.02547 -0.0916 0.9948 0.0338
-11.500 -0.8374 0.02824 0.02373 -0.0939 0.9922 0.0344
-11.250 -0.8107 0.02678 0.02212 -0.0956 0.9886 0.0350
-11.000 -0.7811 0.02550 0.02066 -0.0975 0.9857 0.0357
-10.750 -0.7483 0.02458 0.01956 -0.0997 0.9836 0.0362
-10.500 -0.7191 0.02254 0.01745 -0.1018 0.9818 0.0371
-10.250 -0.6952 0.02148 0.01635 -0.1020 0.9769 0.0378
-10.000 -0.6645 0.02055 0.01537 -0.1034 0.9739 0.0384
-9.750 -0.6312 0.01968 0.01443 -0.1052 0.9717 0.0393
-9.500 -0.5961 0.01888 0.01355 -0.1072 0.9701 0.0403
-9.250 -0.5600 0.01811 0.01268 -0.1094 0.9688 0.0411
-9.000 -0.5328 0.01749 0.01198 -0.1095 0.9639 0.0417
-8.750 -0.5025 0.01648 0.01090 -0.1106 0.9603 0.0426
-8.500 -0.4702 0.01562 0.01001 -0.1120 0.9574 0.0438
-8.250 -0.4359 0.01496 0.00932 -0.1136 0.9549 0.0449
-8.000 -0.4088 0.01447 0.00877 -0.1135 0.9490 0.0463
-7.750 -0.3793 0.01396 0.00820 -0.1138 0.9430 0.0476
-7.500 -0.3481 0.01338 0.00754 -0.1144 0.9379 0.0488
-7.250 -0.3255 0.01279 0.00692 -0.1134 0.9285 0.0508
-7.000 -0.2972 0.01233 0.00640 -0.1133 0.9216 0.0530
-6.750 -0.2727 0.01199 0.00599 -0.1125 0.9120 0.0553
-6.500 -0.2460 0.01146 0.00543 -0.1121 0.9046 0.0601
-6.250 -0.2214 0.01101 0.00498 -0.1114 0.8956 0.0678
-6.000 -0.1956 0.01038 0.00443 -0.1110 0.8876 0.0919
-5.750 -0.1704 0.00998 0.00418 -0.1104 0.8780 0.1257
-5.500 -0.1425 0.00983 0.00401 -0.1102 0.8697 0.1413
-5.250 -0.1159 0.00970 0.00386 -0.1097 0.8591 0.1509
-5.000 -0.0880 0.00964 0.00371 -0.1094 0.8494 0.1591
-4.750 -0.0611 0.00949 0.00356 -0.1090 0.8378 0.1668
-4.500 -0.0337 0.00943 0.00343 -0.1086 0.8261 0.1734
-4.250 -0.0064 0.00931 0.00327 -0.1082 0.8148 0.1794
-4.000 0.0208 0.00924 0.00315 -0.1078 0.8024 0.1854
-3.750 0.0482 0.00922 0.00303 -0.1074 0.7895 0.1905
-3.500 0.0752 0.00913 0.00294 -0.1070 0.7772 0.1983
-3.250 0.1026 0.00915 0.00287 -0.1067 0.7652 0.2051
-3.000 0.1297 0.00909 0.00280 -0.1063 0.7535 0.2121
-2.750 0.1571 0.00912 0.00277 -0.1060 0.7422 0.2195
-2.500 0.1842 0.00911 0.00272 -0.1056 0.7313 0.2267
-2.250 0.2112 0.00912 0.00268 -0.1052 0.7191 0.2330
-2.000 0.2385 0.00914 0.00262 -0.1048 0.7070 0.2385
-1.750 0.2651 0.00909 0.00257 -0.1043 0.6955 0.2453
-1.500 0.2923 0.00913 0.00255 -0.1039 0.6839 0.2522
-1.250 0.3193 0.00911 0.00251 -0.1035 0.6719 0.2589
-1.000 0.3461 0.00913 0.00251 -0.1031 0.6598 0.2655
-0.750 0.3729 0.00920 0.00249 -0.1026 0.6469 0.2717
-0.500 0.3996 0.00916 0.00247 -0.1022 0.6338 0.2784
-0.250 0.4265 0.00920 0.00247 -0.1018 0.6209 0.2848
0.000 0.4530 0.00927 0.00247 -0.1013 0.6066 0.2909
0.250 0.4790 0.00929 0.00248 -0.1008 0.5906 0.2975
0.500 0.5051 0.00938 0.00249 -0.1002 0.5736 0.3037
0.750 0.5310 0.00945 0.00250 -0.0996 0.5570 0.3093
1.000 0.5567 0.00952 0.00254 -0.0991 0.5409 0.3152
1.250 0.5825 0.00963 0.00259 -0.0985 0.5255 0.3211
1.750 0.6341 0.00981 0.00271 -0.0974 0.4980 0.3333
2.000 0.6601 0.00993 0.00278 -0.0969 0.4865 0.3400
2.250 0.6855 0.01004 0.00286 -0.0963 0.4759 0.3464
2.500 0.7117 0.01011 0.00295 -0.0959 0.4664 0.3534
2.750 0.7374 0.01025 0.00305 -0.0953 0.4581 0.3603
3.000 0.7634 0.01031 0.00315 -0.0949 0.4496 0.3688
3.250 0.7888 0.01045 0.00327 -0.0943 0.4415 0.3782
3.500 0.8149 0.01050 0.00338 -0.0938 0.4340 0.3896
3.750 0.8400 0.01061 0.00351 -0.0932 0.4270 0.4037
4.000 0.8659 0.01065 0.00365 -0.0928 0.4210 0.4232
4.250 0.8911 0.01066 0.00379 -0.0922 0.4146 0.4585
4.500 0.9309 0.00978 0.00409 -0.0949 0.4075 1.0000
4.750 0.9566 0.00991 0.00422 -0.0943 0.4006 1.0000
5.000 0.9809 0.01012 0.00436 -0.0935 0.3933 1.0000
5.250 1.0061 0.01025 0.00450 -0.0929 0.3847 1.0000
5.750 1.0548 0.01061 0.00480 -0.0914 0.3661 1.0000
6.000 1.0784 0.01082 0.00497 -0.0905 0.3565 1.0000
6.250 1.1026 0.01100 0.00514 -0.0898 0.3462 1.0000
6.500 1.1263 0.01120 0.00533 -0.0889 0.3356 1.0000
6.750 1.1490 0.01145 0.00553 -0.0879 0.3231 1.0000
7.000 1.1711 0.01172 0.00576 -0.0869 0.3083 1.0000
7.250 1.1924 0.01203 0.00601 -0.0856 0.2892 1.0000
7.500 1.2109 0.01249 0.00633 -0.0840 0.2632 1.0000
7.750 1.2256 0.01316 0.00680 -0.0819 0.2250 1.0000
8.000 1.2385 0.01392 0.00735 -0.0794 0.1944 1.0000
8.250 1.2529 0.01450 0.00785 -0.0771 0.1795 1.0000
8.500 1.2674 0.01501 0.00832 -0.0749 0.1693 1.0000
8.750 1.2801 0.01560 0.00886 -0.0723 0.1588 1.0000
9.000 1.2936 0.01617 0.00939 -0.0700 0.1455 1.0000
9.250 1.3046 0.01689 0.00997 -0.0674 0.1105 1.0000
9.500 1.3014 0.01836 0.01116 -0.0630 0.0758 1.0000
9.750 1.3091 0.01930 0.01211 -0.0602 0.0674 1.0000
10.000 1.3169 0.02026 0.01310 -0.0575 0.0612 1.0000
10.250 1.3259 0.02119 0.01404 -0.0551 0.0566 1.0000
10.500 1.3344 0.02219 0.01507 -0.0528 0.0530 1.0000
10.750 1.3451 0.02309 0.01599 -0.0509 0.0501 1.0000
11.000 1.3515 0.02429 0.01721 -0.0487 0.0477 1.0000
11.250 1.3590 0.02548 0.01846 -0.0467 0.0458 1.0000
11.500 1.3683 0.02661 0.01965 -0.0450 0.0442 1.0000
11.750 1.3757 0.02792 0.02100 -0.0434 0.0427 1.0000
12.000 1.3798 0.02954 0.02265 -0.0417 0.0413 1.0000
12.250 1.3786 0.03169 0.02486 -0.0399 0.0401 1.0000
12.500 1.3856 0.03326 0.02652 -0.0387 0.0393 1.0000
12.750 1.3911 0.03504 0.02838 -0.0376 0.0383 1.0000
13.000 1.3958 0.03695 0.03036 -0.0367 0.0372 1.0000
13.250 1.3988 0.03909 0.03255 -0.0359 0.0363 1.0000
13.500 1.3978 0.04171 0.03523 -0.0351 0.0355 1.0000
13.750 1.3928 0.04483 0.03842 -0.0345 0.0348 1.0000
14.000 1.3892 0.04792 0.04160 -0.0340 0.0342 1.0000
14.250 1.3925 0.05038 0.04416 -0.0338 0.0336 1.0000
14.500 1.3939 0.05311 0.04698 -0.0337 0.0329 1.0000
14.750 1.3950 0.05594 0.04988 -0.0337 0.0322 1.0000
15.000 1.3952 0.05893 0.05294 -0.0338 0.0315 1.0000
15.250 1.3950 0.06206 0.05613 -0.0340 0.0310 1.0000
15.500 1.3932 0.06541 0.05955 -0.0344 0.0305 1.0000
15.750 1.3892 0.06903 0.06321 -0.0348 0.0299 1.0000
16.000 1.3851 0.07264 0.06687 -0.0351 0.0292 1.0000
16.250 1.3872 0.07570 0.07003 -0.0356 0.0288 1.0000
16.500 1.3885 0.07888 0.07330 -0.0362 0.0284 1.0000
16.750 1.3895 0.08212 0.07663 -0.0368 0.0279 1.0000
17.000 1.3905 0.08537 0.07996 -0.0375 0.0273 1.0000
17.250 1.3914 0.08870 0.08335 -0.0383 0.0268 1.0000
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