GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 682 AIRFOIL (goe682-il) Reynolds number: 200,000 Max Cl/Cd: 75.3 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe682-il-200000-n5.txt Download as CSV file: xf-goe682-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 682 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3551 0.08922 0.08564 -0.0419 1.0000 0.0317
-9.000 -0.3684 0.08570 0.08219 -0.0416 1.0000 0.0319
-8.750 -0.3829 0.07727 0.07382 -0.0489 0.9943 0.0328
-8.500 -0.3647 0.07519 0.07173 -0.0518 0.9885 0.0335
-8.250 -0.3481 0.07215 0.06869 -0.0563 0.9812 0.0342
-8.000 -0.3351 0.06540 0.06191 -0.0659 0.9711 0.0346
-7.750 -0.3217 0.05654 0.05294 -0.0782 0.9611 0.0352
-7.500 -0.3221 0.03861 0.03432 -0.0950 0.9469 0.0367
-7.250 -0.3078 0.03095 0.02583 -0.0995 0.9389 0.0380
-7.000 -0.2884 0.02737 0.02165 -0.1004 0.9302 0.0388
-6.750 -0.2628 0.02504 0.01880 -0.1013 0.9237 0.0397
-6.500 -0.2375 0.02327 0.01676 -0.1017 0.9162 0.0407
-6.250 -0.2081 0.02210 0.01545 -0.1025 0.9107 0.0416
-6.000 -0.1823 0.02105 0.01421 -0.1025 0.9023 0.0422
-5.750 -0.1513 0.01999 0.01295 -0.1033 0.8969 0.0431
-5.500 -0.1261 0.01910 0.01190 -0.1029 0.8874 0.0439
-5.250 -0.0955 0.01821 0.01081 -0.1035 0.8813 0.0449
-5.000 -0.0697 0.01749 0.00993 -0.1031 0.8717 0.0460
-4.750 -0.0398 0.01686 0.00912 -0.1034 0.8646 0.0476
-4.500 -0.0133 0.01633 0.00845 -0.1030 0.8544 0.0486
-4.250 0.0139 0.01555 0.00758 -0.1027 0.8441 0.0498
-4.000 0.0416 0.01495 0.00692 -0.1026 0.8330 0.0512
-3.750 0.0676 0.01452 0.00644 -0.1021 0.8205 0.0526
-3.500 0.0942 0.01415 0.00599 -0.1017 0.8098 0.0545
-3.250 0.1216 0.01379 0.00555 -0.1014 0.8008 0.0567
-3.000 0.1479 0.01354 0.00522 -0.1009 0.7904 0.0592
-2.750 0.1741 0.01316 0.00482 -0.1005 0.7811 0.0630
-2.500 0.2008 0.01291 0.00452 -0.1001 0.7716 0.0671
-2.250 0.2272 0.01271 0.00425 -0.0997 0.7619 0.0715
-2.000 0.2539 0.01245 0.00395 -0.0993 0.7532 0.0780
-1.750 0.2801 0.01227 0.00375 -0.0988 0.7435 0.0874
-1.500 0.3063 0.01202 0.00358 -0.0984 0.7345 0.1069
-1.250 0.3322 0.01179 0.00351 -0.0980 0.7251 0.1537
-1.000 0.3585 0.01166 0.00347 -0.0976 0.7163 0.1962
-0.750 0.3850 0.01158 0.00340 -0.0972 0.7076 0.2272
-0.500 0.4110 0.01148 0.00337 -0.0968 0.6982 0.2573
0.000 0.4623 0.01122 0.00333 -0.0958 0.6801 0.3444
0.250 0.4851 0.01081 0.00334 -0.0948 0.6700 0.4755
0.750 0.5724 0.00983 0.00336 -0.1006 0.6441 1.0000
1.000 0.5966 0.00994 0.00337 -0.0997 0.6317 1.0000
1.250 0.6207 0.01007 0.00338 -0.0988 0.6188 1.0000
1.500 0.6448 0.01020 0.00339 -0.0979 0.6050 1.0000
1.750 0.6690 0.01034 0.00343 -0.0970 0.5923 1.0000
2.000 0.6934 0.01048 0.00348 -0.0962 0.5802 1.0000
2.250 0.7179 0.01062 0.00356 -0.0954 0.5679 1.0000
2.500 0.7422 0.01077 0.00364 -0.0946 0.5549 1.0000
2.750 0.7663 0.01093 0.00373 -0.0938 0.5416 1.0000
3.000 0.7905 0.01110 0.00383 -0.0929 0.5286 1.0000
3.250 0.8144 0.01128 0.00395 -0.0921 0.5151 1.0000
3.750 0.8615 0.01169 0.00422 -0.0903 0.4857 1.0000
4.000 0.8847 0.01192 0.00438 -0.0893 0.4708 1.0000
4.250 0.9079 0.01216 0.00457 -0.0884 0.4567 1.0000
4.500 0.9311 0.01242 0.00478 -0.0875 0.4434 1.0000
4.750 0.9540 0.01268 0.00500 -0.0865 0.4303 1.0000
5.000 0.9766 0.01297 0.00525 -0.0855 0.4172 1.0000
5.250 0.9989 0.01327 0.00550 -0.0845 0.4033 1.0000
5.500 1.0209 0.01359 0.00578 -0.0834 0.3886 1.0000
5.750 1.0426 0.01391 0.00608 -0.0823 0.3733 1.0000
6.000 1.0641 0.01424 0.00638 -0.0812 0.3582 1.0000
6.250 1.0852 0.01459 0.00671 -0.0800 0.3426 1.0000
6.500 1.1058 0.01496 0.00705 -0.0787 0.3269 1.0000
6.750 1.1256 0.01537 0.00743 -0.0774 0.3109 1.0000
7.000 1.1445 0.01581 0.00783 -0.0759 0.2949 1.0000
7.250 1.1627 0.01629 0.00825 -0.0743 0.2809 1.0000
7.500 1.1812 0.01676 0.00870 -0.0728 0.2693 1.0000
7.750 1.1999 0.01722 0.00919 -0.0713 0.2599 1.0000
8.250 1.2349 0.01821 0.01018 -0.0681 0.2423 1.0000
8.500 1.2497 0.01876 0.01071 -0.0660 0.2331 1.0000
8.750 1.2644 0.01929 0.01126 -0.0640 0.2233 1.0000
9.000 1.2796 0.01981 0.01182 -0.0620 0.2146 1.0000
9.250 1.2929 0.02043 0.01243 -0.0599 0.2057 1.0000
9.500 1.3084 0.02095 0.01302 -0.0581 0.1961 1.0000
9.750 1.3215 0.02159 0.01368 -0.0561 0.1860 1.0000
10.000 1.3338 0.02228 0.01439 -0.0541 0.1728 1.0000
10.250 1.3460 0.02300 0.01512 -0.0522 0.1569 1.0000
10.500 1.3567 0.02385 0.01596 -0.0501 0.1391 1.0000
10.750 1.3632 0.02500 0.01701 -0.0478 0.1160 1.0000
11.000 1.3642 0.02659 0.01843 -0.0451 0.0912 1.0000
11.250 1.3648 0.02832 0.02006 -0.0426 0.0736 1.0000
11.500 1.3662 0.03008 0.02178 -0.0404 0.0566 1.0000
11.750 1.3642 0.03221 0.02382 -0.0382 0.0403 1.0000
12.000 1.3635 0.03432 0.02593 -0.0363 0.0320 1.0000
12.250 1.3635 0.03648 0.02813 -0.0348 0.0279 1.0000
12.500 1.3652 0.03856 0.03032 -0.0335 0.0254 1.0000
12.750 1.3649 0.04093 0.03278 -0.0323 0.0235 1.0000
13.000 1.3624 0.04363 0.03556 -0.0314 0.0221 1.0000
13.250 1.3625 0.04617 0.03824 -0.0307 0.0210 1.0000
13.500 1.3615 0.04892 0.04113 -0.0302 0.0200 1.0000
13.750 1.3587 0.05199 0.04432 -0.0299 0.0194 1.0000
14.000 1.3538 0.05543 0.04791 -0.0299 0.0187 1.0000
14.250 1.3474 0.05922 0.05181 -0.0302 0.0181 1.0000
14.500 1.3394 0.06338 0.05610 -0.0308 0.0177 1.0000
14.750 1.3308 0.06781 0.06066 -0.0316 0.0174 1.0000
15.000 1.3248 0.07204 0.06504 -0.0325 0.0171 1.0000
15.250 1.3184 0.07644 0.06958 -0.0336 0.0168 1.0000
15.500 1.3110 0.08113 0.07441 -0.0350 0.0165 1.0000
15.750 1.3041 0.08587 0.07929 -0.0365 0.0162 1.0000
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Polar data table (+)
Polar graphs
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