GOE 685 AIRFOIL (goe685-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 685 AIRFOIL (goe685-il) Reynolds number: 100,000 Max Cl/Cd: 52.47 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe685-il-100000.txt Download as CSV file: xf-goe685-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3261 0.09571 0.09078 -0.0316 1.0000 0.1639
-8.000 -0.6163 0.04632 0.04081 -0.0626 1.0000 0.0937
-7.750 -0.6204 0.04044 0.03434 -0.0640 1.0000 0.0939
-7.500 -0.6106 0.03786 0.03163 -0.0634 1.0000 0.0951
-7.250 -0.5966 0.03691 0.03071 -0.0622 1.0000 0.0973
-7.000 -0.5828 0.03512 0.02871 -0.0617 1.0000 0.0997
-6.750 -0.5683 0.03261 0.02576 -0.0617 1.0000 0.1024
-6.500 -0.5391 0.02986 0.02234 -0.0640 0.9965 0.1059
-6.250 -0.5003 0.02907 0.02167 -0.0668 0.9898 0.1108
-6.000 -0.4600 0.02773 0.01995 -0.0700 0.9831 0.1193
-5.750 -0.4220 0.02721 0.01940 -0.0725 0.9747 0.1293
-5.500 -0.3781 0.02650 0.01853 -0.0758 0.9671 0.1458
-5.250 -0.3385 0.02670 0.01901 -0.0781 0.9568 0.1651
-5.000 -0.3000 0.02703 0.01931 -0.0801 0.9465 0.1885
-4.750 -0.2541 0.02767 0.02001 -0.0832 0.9386 0.2083
-4.500 -0.2231 0.02807 0.02036 -0.0837 0.9278 0.2230
-4.250 -0.1764 0.02875 0.02109 -0.0868 0.9215 0.2394
-4.000 -0.1488 0.02962 0.02220 -0.0862 0.9101 0.2504
-3.750 -0.1024 0.02981 0.02240 -0.0892 0.9046 0.2650
-3.500 -0.0765 0.02921 0.02159 -0.0892 0.8933 0.2753
-3.250 -0.0293 0.02870 0.02099 -0.0925 0.8880 0.2866
-3.000 -0.0022 0.02817 0.02038 -0.0925 0.8770 0.2940
-2.750 0.0453 0.02739 0.01942 -0.0959 0.8717 0.3046
-2.500 0.0763 0.02679 0.01876 -0.0964 0.8617 0.3117
-2.250 0.1192 0.02600 0.01784 -0.0988 0.8552 0.3209
-2.000 0.1521 0.02532 0.01704 -0.0995 0.8457 0.3283
-1.750 0.1914 0.02461 0.01626 -0.1010 0.8381 0.3377
-1.500 0.2227 0.02398 0.01553 -0.1013 0.8279 0.3453
-1.250 0.2619 0.02323 0.01471 -0.1026 0.8203 0.3549
-1.000 0.2904 0.02273 0.01417 -0.1023 0.8085 0.3638
-0.750 0.3314 0.02197 0.01325 -0.1038 0.8016 0.3759
-0.500 0.3576 0.02150 0.01285 -0.1031 0.7884 0.3841
-0.250 0.3881 0.02105 0.01232 -0.1030 0.7768 0.3951
0.000 0.4245 0.02043 0.01164 -0.1037 0.7678 0.4081
0.250 0.4512 0.02008 0.01133 -0.1030 0.7538 0.4188
0.500 0.4796 0.01979 0.01100 -0.1026 0.7405 0.4305
0.750 0.5099 0.01952 0.01066 -0.1025 0.7284 0.4440
1.000 0.5409 0.01919 0.01034 -0.1024 0.7168 0.4577
1.250 0.5666 0.01909 0.01029 -0.1017 0.7026 0.4713
1.500 0.5931 0.01900 0.01023 -0.1011 0.6892 0.4868
1.750 0.6217 0.01886 0.01011 -0.1008 0.6774 0.5047
2.000 0.6504 0.01875 0.01004 -0.1005 0.6655 0.5268
2.250 0.6756 0.01873 0.01016 -0.0998 0.6525 0.5535
2.500 0.7021 0.01852 0.01018 -0.0992 0.6413 0.6019
2.750 0.7495 0.01762 0.01000 -0.1021 0.6298 1.0000
3.000 0.7737 0.01799 0.01025 -0.1014 0.6180 1.0000
3.250 0.8016 0.01828 0.01037 -0.1012 0.6093 1.0000
3.500 0.8262 0.01863 0.01066 -0.1005 0.5995 1.0000
3.750 0.8521 0.01897 0.01091 -0.0999 0.5907 1.0000
4.000 0.8776 0.01926 0.01115 -0.0993 0.5815 1.0000
4.250 0.9022 0.01964 0.01150 -0.0986 0.5728 1.0000
4.500 0.9280 0.01994 0.01174 -0.0980 0.5642 1.0000
4.750 0.9521 0.02035 0.01215 -0.0972 0.5557 1.0000
5.000 0.9778 0.02065 0.01242 -0.0966 0.5473 1.0000
5.250 1.0013 0.02105 0.01283 -0.0957 0.5384 1.0000
5.500 1.0273 0.02133 0.01308 -0.0951 0.5300 1.0000
5.750 1.0504 0.02181 0.01362 -0.0942 0.5220 1.0000
6.000 1.0754 0.02217 0.01398 -0.0935 0.5138 1.0000
6.250 1.0988 0.02261 0.01447 -0.0926 0.5053 1.0000
6.500 1.1239 0.02290 0.01476 -0.0919 0.4963 1.0000
6.750 1.1454 0.02334 0.01527 -0.0907 0.4865 1.0000
7.000 1.1743 0.02348 0.01532 -0.0904 0.4770 1.0000
7.250 1.1917 0.02394 0.01592 -0.0886 0.4656 1.0000
7.500 1.2146 0.02419 0.01618 -0.0875 0.4542 1.0000
7.750 1.2398 0.02426 0.01616 -0.0866 0.4415 1.0000
8.000 1.2591 0.02442 0.01637 -0.0848 0.4276 1.0000
8.250 1.2758 0.02469 0.01673 -0.0828 0.4138 1.0000
8.500 1.2938 0.02498 0.01707 -0.0809 0.4009 1.0000
8.750 1.3130 0.02520 0.01733 -0.0793 0.3882 1.0000
9.000 1.3306 0.02536 0.01749 -0.0773 0.3744 1.0000
9.250 1.3423 0.02561 0.01784 -0.0745 0.3597 1.0000
9.500 1.3521 0.02592 0.01828 -0.0715 0.3448 1.0000
9.750 1.3603 0.02627 0.01876 -0.0683 0.3294 1.0000
10.000 1.3652 0.02666 0.01922 -0.0646 0.3125 1.0000
10.250 1.3641 0.02719 0.01977 -0.0601 0.2931 1.0000
10.500 1.3601 0.02803 0.02065 -0.0557 0.2685 1.0000
10.750 1.3526 0.02933 0.02184 -0.0514 0.2388 1.0000
11.000 1.3396 0.03132 0.02361 -0.0472 0.2075 1.0000
11.250 1.3237 0.03397 0.02602 -0.0436 0.1814 1.0000
11.500 1.3073 0.03705 0.02892 -0.0406 0.1608 1.0000
11.750 1.2947 0.04021 0.03199 -0.0383 0.1429 1.0000
12.000 1.2873 0.04317 0.03495 -0.0368 0.1277 1.0000
12.250 1.2812 0.04617 0.03792 -0.0357 0.1178 1.0000
12.500 1.2794 0.04891 0.04068 -0.0347 0.1100 1.0000
12.750 1.2756 0.05187 0.04355 -0.0339 0.1047 1.0000
13.000 1.2764 0.05446 0.04617 -0.0331 0.0996 1.0000
13.250 1.2779 0.05692 0.04851 -0.0323 0.0955 1.0000
13.500 1.2871 0.05870 0.05028 -0.0311 0.0915 1.0000
13.750 1.2992 0.06024 0.05180 -0.0299 0.0878 1.0000
14.000 1.3294 0.06043 0.05172 -0.0278 0.0832 1.0000
14.250 1.3411 0.06242 0.05389 -0.0270 0.0807 1.0000
14.500 1.3591 0.06409 0.05565 -0.0260 0.0780 1.0000
14.750 1.4186 0.06459 0.05586 -0.0249 0.0731 1.0000
15.000 1.4142 0.06763 0.05920 -0.0242 0.0721 1.0000
15.250 1.4130 0.07082 0.06266 -0.0237 0.0711 1.0000
15.500 1.4110 0.07427 0.06638 -0.0234 0.0701 1.0000
15.750 1.4066 0.07801 0.07038 -0.0233 0.0692 1.0000
16.000 1.3997 0.08203 0.07464 -0.0235 0.0683 1.0000
16.250 1.3914 0.08630 0.07913 -0.0240 0.0675 1.0000
16.500 1.3824 0.09078 0.08381 -0.0248 0.0668 1.0000
16.750 1.3728 0.09547 0.08871 -0.0259 0.0661 1.0000
17.000 1.3627 0.10039 0.09382 -0.0272 0.0655 1.0000
17.250 1.3099 0.11059 0.10448 -0.0328 0.0668 1.0000
17.500 1.2514 0.12385 0.11817 -0.0411 0.0688 1.0000
17.750 1.1949 0.13901 0.13363 -0.0509 0.0709 1.0000
18.000 1.1480 0.15440 0.14917 -0.0606 0.0727 1.0000
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