GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 B AIRFOIL (goe802b-il) Reynolds number: 200,000 Max Cl/Cd: 76.28 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802b-il-200000.txt Download as CSV file: xf-goe802b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 B 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3036 0.10223 0.09891 -0.0316 1.0000 0.0352
-8.250 -0.3270 0.10230 0.09908 -0.0273 1.0000 0.0352
-8.000 -0.3451 0.10177 0.09863 -0.0254 1.0000 0.0352
-7.750 -0.3416 0.09790 0.09480 -0.0231 0.9994 0.0354
-7.500 -0.3238 0.09329 0.09018 -0.0238 0.9969 0.0359
-7.250 -0.2992 0.08888 0.08576 -0.0291 0.9931 0.0367
-7.000 -0.2751 0.08475 0.08160 -0.0351 0.9871 0.0377
-6.750 -0.2454 0.08034 0.07715 -0.0430 0.9823 0.0393
-6.500 -0.1926 0.07570 0.07226 -0.0640 0.9722 0.0413
-6.250 -0.1767 0.07091 0.06756 -0.0630 0.9696 0.0417
-6.000 -0.1492 0.06680 0.06344 -0.0668 0.9669 0.0425
-5.750 -0.1219 0.06328 0.05986 -0.0713 0.9604 0.0437
-5.500 -0.0862 0.05942 0.05590 -0.0778 0.9552 0.0458
-5.250 -0.0338 0.05520 0.05136 -0.0885 0.9508 0.0479
-5.000 -0.0147 0.05180 0.04801 -0.0894 0.9434 0.0486
-4.750 0.0134 0.04888 0.04502 -0.0921 0.9369 0.0504
-4.250 0.0794 0.04360 0.03929 -0.0980 0.9212 0.0546
-4.000 0.1040 0.04065 0.03631 -0.0991 0.9148 0.0556
-3.750 0.1258 0.03859 0.03415 -0.0991 0.9033 0.0573
-3.500 0.1631 0.03863 0.03355 -0.0998 0.8950 0.0607
-3.250 0.1805 0.03484 0.02991 -0.0995 0.8837 0.0613
-3.000 0.2032 0.03265 0.02764 -0.0994 0.8746 0.0628
-2.750 0.2290 0.03122 0.02601 -0.0990 0.8641 0.0658
-2.500 0.2555 0.02976 0.02430 -0.0987 0.8540 0.0677
-2.250 0.2801 0.02802 0.02244 -0.0984 0.8439 0.0698
-2.000 0.3099 0.02859 0.02254 -0.0974 0.8316 0.0724
-1.750 0.3340 0.02584 0.01976 -0.0973 0.8216 0.0731
-1.500 0.3595 0.02431 0.01810 -0.0970 0.8090 0.0746
-1.250 0.3870 0.02367 0.01722 -0.0964 0.7962 0.0767
-1.000 0.4164 0.02433 0.01743 -0.0954 0.7841 0.0773
-0.750 0.4417 0.02180 0.01490 -0.0954 0.7713 0.0779
-0.500 0.4683 0.02060 0.01357 -0.0951 0.7569 0.0793
-0.250 0.4962 0.02045 0.01316 -0.0945 0.7420 0.0815
0.000 0.5241 0.02040 0.01284 -0.0938 0.7268 0.0818
0.250 0.5515 0.02003 0.01224 -0.0933 0.7117 0.0819
0.500 0.5788 0.01945 0.01147 -0.0928 0.6967 0.0819
0.750 0.6058 0.01882 0.01068 -0.0924 0.6811 0.0819
1.000 0.6327 0.01818 0.00991 -0.0921 0.6650 0.0818
1.500 0.6865 0.01716 0.00864 -0.0913 0.6338 0.0818
1.750 0.7131 0.01647 0.00787 -0.0911 0.6194 0.0855
2.000 0.7401 0.01662 0.00783 -0.0906 0.6054 0.0865
2.250 0.7667 0.01617 0.00728 -0.0903 0.5918 0.0907
2.500 0.7931 0.01564 0.00672 -0.0900 0.5776 0.0982
2.750 0.8180 0.01411 0.00543 -0.0897 0.5647 0.1312
3.000 0.8427 0.01187 0.00507 -0.0893 0.5527 1.0000
3.250 0.8687 0.01212 0.00516 -0.0889 0.5387 1.0000
3.500 0.8943 0.01235 0.00530 -0.0885 0.5239 1.0000
3.750 0.9200 0.01261 0.00545 -0.0881 0.5099 1.0000
4.000 0.9455 0.01288 0.00562 -0.0877 0.4971 1.0000
4.250 0.9711 0.01315 0.00578 -0.0873 0.4846 1.0000
4.500 0.9967 0.01339 0.00601 -0.0870 0.4726 1.0000
4.750 1.0223 0.01371 0.00624 -0.0867 0.4629 1.0000
5.000 1.0479 0.01396 0.00649 -0.0864 0.4523 1.0000
5.250 1.0733 0.01426 0.00674 -0.0861 0.4427 1.0000
5.500 1.0985 0.01453 0.00699 -0.0857 0.4325 1.0000
5.750 1.1236 0.01483 0.00729 -0.0853 0.4228 1.0000
6.000 1.1484 0.01513 0.00754 -0.0849 0.4131 1.0000
6.250 1.1729 0.01540 0.00785 -0.0845 0.4024 1.0000
6.500 1.1972 0.01575 0.00813 -0.0840 0.3926 1.0000
6.750 1.2212 0.01601 0.00846 -0.0835 0.3816 1.0000
7.000 1.2447 0.01634 0.00879 -0.0829 0.3707 1.0000
7.250 1.2675 0.01671 0.00908 -0.0822 0.3590 1.0000
7.500 1.2900 0.01699 0.00944 -0.0815 0.3459 1.0000
7.750 1.3123 0.01735 0.00984 -0.0807 0.3337 1.0000
8.000 1.3337 0.01777 0.01023 -0.0798 0.3213 1.0000
8.250 1.3544 0.01819 0.01065 -0.0789 0.3074 1.0000
8.500 1.3747 0.01860 0.01110 -0.0778 0.2922 1.0000
8.750 1.3936 0.01907 0.01159 -0.0766 0.2753 1.0000
9.000 1.4112 0.01961 0.01211 -0.0753 0.2570 1.0000
9.250 1.4273 0.02025 0.01268 -0.0737 0.2389 1.0000
9.500 1.4428 0.02094 0.01334 -0.0721 0.2220 1.0000
9.750 1.4570 0.02171 0.01408 -0.0703 0.2072 1.0000
10.000 1.4700 0.02251 0.01487 -0.0684 0.1940 1.0000
10.250 1.4804 0.02335 0.01571 -0.0661 0.1831 1.0000
10.500 1.4879 0.02442 0.01671 -0.0635 0.1740 1.0000
10.750 1.4999 0.02529 0.01767 -0.0617 0.1652 1.0000
11.000 1.5066 0.02652 0.01886 -0.0594 0.1576 1.0000
11.250 1.5182 0.02747 0.01994 -0.0578 0.1495 1.0000
11.750 1.5353 0.02989 0.02248 -0.0543 0.1357 1.0000
12.000 1.5418 0.03132 0.02393 -0.0526 0.1298 1.0000
12.250 1.5498 0.03269 0.02540 -0.0511 0.1239 1.0000
12.500 1.5581 0.03407 0.02689 -0.0499 0.1176 1.0000
12.750 1.5609 0.03597 0.02878 -0.0485 0.1125 1.0000
13.000 1.5715 0.03727 0.03027 -0.0476 0.1066 1.0000
13.250 1.5759 0.03917 0.03221 -0.0466 0.1009 1.0000
13.500 1.5814 0.04104 0.03419 -0.0458 0.0951 1.0000
13.750 1.5846 0.04322 0.03642 -0.0451 0.0875 1.0000
14.000 1.5872 0.04553 0.03883 -0.0444 0.0813 1.0000
14.250 1.5856 0.04839 0.04174 -0.0440 0.0747 1.0000
14.500 1.5831 0.05144 0.04487 -0.0436 0.0681 1.0000
14.750 1.5744 0.05534 0.04879 -0.0436 0.0625 1.0000
15.000 1.5695 0.05895 0.05252 -0.0436 0.0561 1.0000
15.250 1.5585 0.06349 0.05712 -0.0441 0.0511 1.0000
15.500 1.5503 0.06780 0.06153 -0.0447 0.0449 1.0000
15.750 1.5395 0.07261 0.06643 -0.0456 0.0403 1.0000
16.000 1.5278 0.07766 0.07157 -0.0467 0.0365 1.0000
16.250 1.5148 0.08304 0.07703 -0.0480 0.0342 1.0000
16.500 1.5024 0.08845 0.08255 -0.0495 0.0324 1.0000
16.750 1.4891 0.09410 0.08831 -0.0512 0.0312 1.0000
17.000 1.4747 0.10001 0.09433 -0.0531 0.0302 1.0000
17.250 1.4599 0.10615 0.10057 -0.0553 0.0294 1.0000
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Polar data table (+)
Polar graphs
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