GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 383 AIRFOIL (goe383-il) Reynolds number: 200,000 Max Cl/Cd: 62.25 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe383-il-200000.txt Download as CSV file: xf-goe383-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 383 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.0378 0.10683 0.10291 -0.0769 0.8344 0.0946
-11.250 -0.0290 0.10462 0.10064 -0.0765 0.8244 0.0962
-11.000 -0.0722 0.09728 0.09327 -0.0826 0.8213 0.1017
-10.750 -0.0488 0.09572 0.09168 -0.0809 0.8103 0.1023
-10.500 -0.0325 0.09411 0.08999 -0.0797 0.8019 0.1035
-10.250 -0.0224 0.09181 0.08767 -0.0798 0.7939 0.1058
-10.000 -0.0617 0.08369 0.07956 -0.0859 0.7900 0.1114
-9.750 -0.4182 0.04515 0.03937 -0.1048 0.8094 0.0708
-9.500 -0.4034 0.04277 0.03688 -0.1041 0.8020 0.0701
-9.250 -0.3951 0.03996 0.03386 -0.1031 0.7940 0.0688
-9.000 -0.4151 0.03492 0.02754 -0.0985 0.7863 0.0649
-8.750 -0.3961 0.03312 0.02548 -0.0977 0.7803 0.0648
-8.500 -0.3764 0.03153 0.02369 -0.0969 0.7736 0.0647
-8.250 -0.3557 0.03013 0.02207 -0.0961 0.7671 0.0647
-8.000 -0.3339 0.02891 0.02059 -0.0953 0.7617 0.0648
-7.750 -0.3100 0.02755 0.01907 -0.0948 0.7564 0.0652
-7.500 -0.2854 0.02639 0.01790 -0.0946 0.7492 0.0658
-7.250 -0.2602 0.02551 0.01697 -0.0942 0.7425 0.0667
-7.000 -0.2345 0.02473 0.01606 -0.0938 0.7369 0.0676
-6.750 -0.2092 0.02399 0.01525 -0.0934 0.7313 0.0685
-6.500 -0.1834 0.02327 0.01444 -0.0930 0.7259 0.0692
-6.250 -0.1570 0.02259 0.01365 -0.0927 0.7209 0.0700
-6.000 -0.1303 0.02201 0.01293 -0.0923 0.7166 0.0708
-5.750 -0.1038 0.02132 0.01225 -0.0921 0.7124 0.0719
-5.500 -0.0786 0.02075 0.01178 -0.0917 0.7073 0.0732
-5.250 -0.0531 0.02028 0.01132 -0.0913 0.7022 0.0747
-5.000 -0.0271 0.01986 0.01084 -0.0909 0.6977 0.0768
-4.750 -0.0016 0.01940 0.01037 -0.0904 0.6937 0.0792
-4.500 0.0229 0.01908 0.01012 -0.0899 0.6894 0.0820
-4.250 0.0476 0.01878 0.00982 -0.0893 0.6844 0.0851
-4.000 0.0719 0.01839 0.00949 -0.0887 0.6794 0.0891
-3.750 0.0976 0.01804 0.00913 -0.0882 0.6749 0.0948
-3.500 0.1238 0.01779 0.00888 -0.0878 0.6707 0.1048
-3.250 0.1465 0.01740 0.00871 -0.0870 0.6656 0.1299
-3.000 0.1676 0.01672 0.00845 -0.0861 0.6605 0.2023
-2.750 0.1916 0.01632 0.00834 -0.0855 0.6558 0.2802
-2.500 0.2173 0.01604 0.00820 -0.0851 0.6515 0.3346
-2.250 0.2412 0.01585 0.00821 -0.0845 0.6467 0.3899
-2.000 0.2629 0.01556 0.00825 -0.0834 0.6408 0.4601
-1.750 0.2855 0.01524 0.00826 -0.0823 0.6353 0.5423
-1.500 0.3099 0.01505 0.00829 -0.0812 0.6306 0.6255
-1.250 0.3345 0.01510 0.00847 -0.0801 0.6258 0.6851
-1.000 0.3570 0.01512 0.00865 -0.0787 0.6196 0.7298
-0.750 0.3814 0.01513 0.00872 -0.0775 0.6140 0.7705
-0.500 0.4076 0.01516 0.00878 -0.0763 0.6092 0.8063
-0.250 0.4323 0.01533 0.00895 -0.0751 0.6038 0.8363
0.000 0.4550 0.01543 0.00911 -0.0736 0.5969 0.8612
0.250 0.4820 0.01551 0.00914 -0.0728 0.5911 0.8834
0.500 0.5134 0.01565 0.00916 -0.0727 0.5863 0.9033
0.750 0.5433 0.01588 0.00941 -0.0728 0.5797 0.9206
1.000 0.5794 0.01605 0.00954 -0.0741 0.5731 0.9361
1.250 0.6220 0.01618 0.00954 -0.0765 0.5677 0.9497
1.500 0.6678 0.01639 0.00966 -0.0801 0.5615 0.9583
1.750 0.7096 0.01651 0.00975 -0.0831 0.5542 0.9663
2.000 0.7573 0.01656 0.00969 -0.0871 0.5486 0.9734
2.250 0.8051 0.01668 0.00968 -0.0912 0.5433 0.9813
2.500 0.8516 0.01680 0.00984 -0.0953 0.5359 0.9900
2.750 0.9020 0.01679 0.00973 -0.1001 0.5300 0.9968
3.000 0.9381 0.01681 0.00961 -0.1021 0.5255 1.0000
3.250 0.9489 0.01697 0.00983 -0.0997 0.5197 1.0000
3.500 0.9630 0.01704 0.00989 -0.0976 0.5143 1.0000
3.750 0.9805 0.01706 0.00982 -0.0960 0.5097 1.0000
4.000 0.9984 0.01716 0.00983 -0.0944 0.5047 1.0000
4.250 1.0097 0.01732 0.01002 -0.0917 0.4984 1.0000
4.500 1.0273 0.01738 0.01003 -0.0899 0.4931 1.0000
4.750 1.0503 0.01748 0.01000 -0.0891 0.4887 1.0000
5.000 1.0644 0.01776 0.01031 -0.0869 0.4836 1.0000
5.250 1.0810 0.01797 0.01053 -0.0850 0.4784 1.0000
5.500 1.1019 0.01813 0.01063 -0.0839 0.4739 1.0000
5.750 1.1292 0.01834 0.01069 -0.0839 0.4697 1.0000
6.000 1.1419 0.01868 0.01113 -0.0814 0.4647 1.0000
6.250 1.1607 0.01895 0.01141 -0.0800 0.4598 1.0000
6.500 1.1838 0.01917 0.01156 -0.0794 0.4553 1.0000
6.750 1.2113 0.01946 0.01175 -0.0795 0.4509 1.0000
7.000 1.2244 0.01986 0.01225 -0.0773 0.4459 1.0000
7.250 1.2438 0.02018 0.01258 -0.0761 0.4410 1.0000
7.500 1.2684 0.02044 0.01279 -0.0757 0.4366 1.0000
7.750 1.2940 0.02083 0.01312 -0.0757 0.4321 1.0000
8.000 1.3054 0.02129 0.01368 -0.0733 0.4270 1.0000
8.250 1.3241 0.02163 0.01403 -0.0720 0.4219 1.0000
8.500 1.3513 0.02193 0.01423 -0.0722 0.4171 1.0000
8.750 1.3675 0.02244 0.01480 -0.0707 0.4123 1.0000
9.000 1.3761 0.02294 0.01538 -0.0679 0.4072 1.0000
9.250 1.3944 0.02332 0.01574 -0.0667 0.4023 1.0000
9.500 1.4307 0.02366 0.01595 -0.0685 0.3974 1.0000
9.750 1.4260 0.02438 0.01684 -0.0637 0.3924 1.0000
10.000 1.4351 0.02496 0.01748 -0.0614 0.3869 1.0000
10.250 1.4580 0.02528 0.01771 -0.0610 0.3815 1.0000
10.500 1.4655 0.02603 0.01853 -0.0586 0.3758 1.0000
10.750 1.4682 0.02687 0.01946 -0.0557 0.3697 1.0000
11.000 1.4864 0.02728 0.01982 -0.0548 0.3641 1.0000
11.250 1.4951 0.02816 0.02074 -0.0529 0.3586 1.0000
11.500 1.4956 0.02930 0.02199 -0.0503 0.3526 1.0000
11.750 1.5104 0.02992 0.02258 -0.0492 0.3473 1.0000
12.000 1.5202 0.03088 0.02357 -0.0478 0.3418 1.0000
12.250 1.5175 0.03241 0.02522 -0.0454 0.3357 1.0000
12.500 1.5299 0.03319 0.02597 -0.0443 0.3302 1.0000
12.750 1.5340 0.03457 0.02740 -0.0427 0.3244 1.0000
13.000 1.5309 0.03640 0.02933 -0.0409 0.3181 1.0000
13.250 1.5456 0.03709 0.02992 -0.0401 0.3124 1.0000
13.500 1.5377 0.03949 0.03247 -0.0383 0.3062 1.0000
13.750 1.5380 0.04136 0.03439 -0.0371 0.3001 1.0000
14.000 1.5537 0.04210 0.03504 -0.0366 0.2949 1.0000
14.250 1.5450 0.04498 0.03809 -0.0353 0.2894 1.0000
14.500 1.5483 0.04689 0.04005 -0.0346 0.2845 1.0000
14.750 1.5676 0.04734 0.04038 -0.0342 0.2799 1.0000
15.000 1.5564 0.05071 0.04396 -0.0333 0.2749 1.0000
15.250 1.5568 0.05306 0.04637 -0.0327 0.2700 1.0000
15.500 1.5726 0.05383 0.04707 -0.0324 0.2658 1.0000
15.750 1.5690 0.05668 0.05005 -0.0319 0.2615 1.0000
16.000 1.5650 0.05962 0.05310 -0.0315 0.2570 1.0000
16.250 1.5723 0.06134 0.05482 -0.0312 0.2526 1.0000
16.500 1.5801 0.06301 0.05649 -0.0309 0.2485 1.0000
16.750 1.5687 0.06695 0.06060 -0.0307 0.2440 1.0000
17.000 1.5685 0.06961 0.06332 -0.0306 0.2397 1.0000
17.250 1.5854 0.07020 0.06382 -0.0304 0.2351 1.0000
17.500 1.5670 0.07515 0.06899 -0.0306 0.2309 1.0000
17.750 1.5603 0.07875 0.07269 -0.0308 0.2264 1.0000
18.000 1.5764 0.07942 0.07326 -0.0306 0.2216 1.0000
18.250 1.5551 0.08499 0.07905 -0.0312 0.2171 1.0000
18.500 1.5439 0.08931 0.08347 -0.0318 0.2115 1.0000
18.750 1.5478 0.09162 0.08575 -0.0321 0.2060 1.0000
19.000 1.5243 0.09783 0.09217 -0.0333 0.2004 1.0000
19.250 1.5301 0.09990 0.09416 -0.0337 0.1939 1.0000
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