GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 702 AIRFOIL (goe702-il) Reynolds number: 100,000 Max Cl/Cd: 43.13 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe702-il-100000-n5.txt Download as CSV file: xf-goe702-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 702 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2005 0.09741 0.09157 -0.0566 0.8095 0.0682
-10.500 -0.2060 0.09243 0.08658 -0.0591 0.8021 0.0687
-10.250 -0.2212 0.08598 0.08011 -0.0627 0.7963 0.0697
-10.000 -0.2093 0.08453 0.07865 -0.0628 0.7878 0.0706
-9.750 -0.2070 0.08149 0.07559 -0.0639 0.7794 0.0714
-9.500 -0.2118 0.07738 0.07144 -0.0656 0.7729 0.0723
-9.000 -0.4289 0.04080 0.03395 -0.0874 0.7650 0.0744
-8.750 -0.4344 0.03694 0.02948 -0.0865 0.7578 0.0762
-8.500 -0.4209 0.03543 0.02773 -0.0853 0.7511 0.0776
-8.250 -0.4006 0.03476 0.02705 -0.0846 0.7421 0.0790
-8.000 -0.3830 0.03364 0.02574 -0.0835 0.7354 0.0807
-7.750 -0.3668 0.03209 0.02386 -0.0825 0.7300 0.0827
-7.500 -0.3499 0.03043 0.02182 -0.0817 0.7234 0.0850
-7.250 -0.3268 0.02994 0.02134 -0.0810 0.7173 0.0867
-7.000 -0.3044 0.02928 0.02056 -0.0801 0.7123 0.0890
-6.750 -0.2828 0.02833 0.01937 -0.0794 0.7063 0.0919
-6.500 -0.2604 0.02741 0.01825 -0.0787 0.6998 0.0946
-6.250 -0.2363 0.02693 0.01775 -0.0779 0.6941 0.0970
-6.000 -0.2125 0.02631 0.01696 -0.0772 0.6890 0.1005
-5.750 -0.1888 0.02557 0.01601 -0.0766 0.6818 0.1043
-5.500 -0.1641 0.02510 0.01557 -0.0759 0.6755 0.1072
-5.250 -0.1392 0.02458 0.01490 -0.0752 0.6705 0.1114
-5.000 -0.1145 0.02404 0.01422 -0.0746 0.6631 0.1159
-4.750 -0.0894 0.02361 0.01383 -0.0740 0.6561 0.1197
-4.500 -0.0637 0.02315 0.01321 -0.0733 0.6506 0.1250
-4.250 -0.0386 0.02273 0.01275 -0.0728 0.6428 0.1298
-4.000 -0.0131 0.02237 0.01239 -0.0722 0.6356 0.1350
-3.750 0.0133 0.02197 0.01178 -0.0715 0.6299 0.1412
-3.500 0.0382 0.02165 0.01156 -0.0710 0.6210 0.1464
-3.250 0.0643 0.02132 0.01116 -0.0704 0.6136 0.1530
-3.000 0.0902 0.02099 0.01080 -0.0698 0.6064 0.1593
-2.750 0.1158 0.02076 0.01057 -0.0693 0.5975 0.1665
-2.500 0.1423 0.02043 0.01017 -0.0687 0.5909 0.1743
-2.250 0.1676 0.02026 0.01005 -0.0682 0.5810 0.1827
-2.000 0.1939 0.01999 0.00975 -0.0676 0.5732 0.1918
-1.750 0.2196 0.01983 0.00960 -0.0670 0.5637 0.2024
-1.500 0.2456 0.01962 0.00941 -0.0664 0.5554 0.2137
-1.250 0.2716 0.01949 0.00930 -0.0659 0.5466 0.2275
-1.000 0.2976 0.01937 0.00917 -0.0653 0.5378 0.2438
-0.750 0.3237 0.01929 0.00908 -0.0648 0.5294 0.2622
-0.500 0.3495 0.01924 0.00903 -0.0642 0.5205 0.2820
-0.250 0.3756 0.01921 0.00895 -0.0637 0.5128 0.3017
0.000 0.4012 0.01922 0.00896 -0.0631 0.5044 0.3204
0.250 0.4276 0.01917 0.00886 -0.0626 0.4982 0.3389
0.500 0.4532 0.01924 0.00897 -0.0621 0.4901 0.3570
0.750 0.4795 0.01924 0.00894 -0.0616 0.4834 0.3752
1.000 0.5060 0.01929 0.00895 -0.0612 0.4770 0.3941
1.250 0.5324 0.01936 0.00906 -0.0609 0.4702 0.4143
1.500 0.5590 0.01939 0.00906 -0.0606 0.4648 0.4383
1.750 0.5847 0.01941 0.00914 -0.0601 0.4597 0.4699
2.000 0.6087 0.01938 0.00932 -0.0594 0.4539 0.5172
2.250 0.7013 0.01854 0.00948 -0.0714 0.4462 1.0000
2.500 0.7251 0.01884 0.00961 -0.0706 0.4416 1.0000
2.750 0.7478 0.01918 0.00988 -0.0698 0.4365 1.0000
3.000 0.7710 0.01949 0.01009 -0.0689 0.4321 1.0000
3.250 0.7949 0.01980 0.01025 -0.0681 0.4282 1.0000
3.500 0.8193 0.02012 0.01041 -0.0675 0.4248 1.0000
3.750 0.8406 0.02053 0.01083 -0.0664 0.4202 1.0000
4.000 0.8627 0.02092 0.01117 -0.0655 0.4158 1.0000
4.250 0.8856 0.02127 0.01145 -0.0647 0.4119 1.0000
4.500 0.9097 0.02162 0.01168 -0.0640 0.4086 1.0000
4.750 0.9336 0.02202 0.01199 -0.0633 0.4055 1.0000
5.000 0.9536 0.02253 0.01255 -0.0622 0.4018 1.0000
5.250 0.9744 0.02301 0.01304 -0.0612 0.3981 1.0000
5.500 0.9963 0.02344 0.01345 -0.0603 0.3945 1.0000
5.750 1.0196 0.02384 0.01377 -0.0596 0.3913 1.0000
6.000 1.0446 0.02422 0.01407 -0.0591 0.3884 1.0000
6.250 1.0638 0.02480 0.01469 -0.0580 0.3853 1.0000
6.500 1.0811 0.02544 0.01541 -0.0567 0.3819 1.0000
6.750 1.0999 0.02604 0.01606 -0.0556 0.3787 1.0000
7.000 1.1201 0.02657 0.01660 -0.0546 0.3756 1.0000
7.250 1.1424 0.02703 0.01702 -0.0539 0.3727 1.0000
7.500 1.1674 0.02745 0.01737 -0.0535 0.3701 1.0000
7.750 1.1845 0.02814 0.01812 -0.0522 0.3673 1.0000
8.000 1.1947 0.02904 0.01916 -0.0502 0.3641 1.0000
8.250 1.2067 0.02988 0.02010 -0.0485 0.3610 1.0000
8.500 1.2215 0.03061 0.02088 -0.0470 0.3580 1.0000
8.750 1.2403 0.03119 0.02146 -0.0460 0.3553 1.0000
9.000 1.2639 0.03163 0.02187 -0.0455 0.3528 1.0000
9.250 1.2902 0.03208 0.02228 -0.0454 0.3507 1.0000
9.500 1.2788 0.03363 0.02405 -0.0412 0.3475 1.0000
9.750 1.2673 0.03530 0.02588 -0.0373 0.3443 1.0000
10.000 1.2633 0.03690 0.02759 -0.0348 0.3410 1.0000
10.250 1.2718 0.03801 0.02875 -0.0333 0.3382 1.0000
10.500 1.2924 0.03854 0.02927 -0.0327 0.3358 1.0000
10.750 1.3215 0.03871 0.02943 -0.0326 0.3339 1.0000
11.000 1.2755 0.04320 0.03418 -0.0288 0.3297 1.0000
11.250 1.1706 0.05416 0.04546 -0.0263 0.3206 1.0000
11.500 1.1936 0.05434 0.04564 -0.0258 0.3187 1.0000
11.750 1.2249 0.05378 0.04509 -0.0252 0.3174 1.0000
12.000 1.2621 0.05279 0.04407 -0.0247 0.3164 1.0000
14.000 0.9325 0.12325 0.11537 -0.0402 0.2442 1.0000
14.250 0.9446 0.12482 0.11698 -0.0403 0.2411 1.0000
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Polar data table (+)
Polar graphs
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