GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 400 AIRFOIL (goe400-il) Reynolds number: 100,000 Max Cl/Cd: 61.36 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe400-il-100000-n5.txt Download as CSV file: xf-goe400-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 400 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3982 0.11302 0.10815 -0.0044 1.0000 0.0478
-8.500 -0.3968 0.11120 0.10640 -0.0081 1.0000 0.0481
-8.250 -0.3936 0.10885 0.10410 -0.0119 1.0000 0.0483
-8.000 -0.3800 0.10229 0.09756 -0.0093 1.0000 0.0491
-7.750 -0.3686 0.09827 0.09355 -0.0086 1.0000 0.0503
-7.500 -0.3602 0.09518 0.09049 -0.0093 1.0000 0.0516
-7.250 -0.3523 0.09227 0.08762 -0.0107 1.0000 0.0531
-7.000 -0.3423 0.08942 0.08481 -0.0134 1.0000 0.0568
-6.750 -0.3252 0.08729 0.08270 -0.0259 1.0000 0.0600
-6.500 -0.3089 0.08340 0.07883 -0.0315 1.0000 0.0604
-6.250 -0.3030 0.07918 0.07467 -0.0273 1.0000 0.0613
-6.000 -0.2916 0.07599 0.07148 -0.0272 1.0000 0.0625
-5.750 -0.2784 0.07299 0.06851 -0.0288 1.0000 0.0640
-5.500 -0.2559 0.07052 0.06602 -0.0360 1.0000 0.0709
-5.000 -0.1950 0.05995 0.05521 -0.0500 0.9854 0.0599
-4.750 -0.1712 0.05624 0.05151 -0.0512 0.9710 0.0565
-4.500 -0.1277 0.05156 0.04663 -0.0595 0.9545 0.0579
-4.250 -0.0886 0.04732 0.04218 -0.0656 0.9378 0.0567
-4.000 -0.0492 0.04308 0.03771 -0.0712 0.9206 0.0550
-3.750 -0.0108 0.03903 0.03337 -0.0761 0.9029 0.0541
-3.500 0.0245 0.03570 0.02973 -0.0794 0.8842 0.0554
-3.250 0.0589 0.03238 0.02604 -0.0822 0.8664 0.0571
-3.000 0.0911 0.02919 0.02243 -0.0840 0.8495 0.0567
-2.750 0.1223 0.02620 0.01897 -0.0852 0.8335 0.0567
-2.500 0.1528 0.02337 0.01560 -0.0860 0.8185 0.0572
-2.250 0.1825 0.02089 0.01253 -0.0863 0.8042 0.0584
-2.000 0.2113 0.01901 0.01007 -0.0863 0.7905 0.0600
-1.750 0.2381 0.01878 0.00979 -0.0859 0.7767 0.0628
-1.500 0.2652 0.01847 0.00933 -0.0855 0.7638 0.0669
-1.250 0.2932 0.01752 0.00806 -0.0851 0.7521 0.0705
-1.000 0.3205 0.01706 0.00748 -0.0847 0.7402 0.0737
-0.750 0.3478 0.01671 0.00702 -0.0843 0.7283 0.0796
-0.500 0.3751 0.01639 0.00658 -0.0838 0.7171 0.0890
-0.250 0.4023 0.01617 0.00619 -0.0833 0.7066 0.1034
0.000 0.4294 0.01610 0.00603 -0.0829 0.6956 0.1189
0.250 0.4564 0.01608 0.00596 -0.0827 0.6846 0.1350
0.500 0.4829 0.01606 0.00597 -0.0823 0.6744 0.1531
0.750 0.5096 0.01596 0.00584 -0.0819 0.6643 0.1629
1.000 0.5362 0.01584 0.00567 -0.0814 0.6536 0.1667
1.250 0.5632 0.01575 0.00557 -0.0810 0.6439 0.1722
1.500 0.5902 0.01571 0.00548 -0.0805 0.6339 0.1770
1.750 0.6172 0.01570 0.00544 -0.0802 0.6232 0.1808
2.000 0.6441 0.01568 0.00543 -0.0798 0.6134 0.1853
2.250 0.6709 0.01571 0.00544 -0.0793 0.6034 0.1917
2.500 0.6978 0.01574 0.00553 -0.0790 0.5925 0.2003
2.750 0.7246 0.01577 0.00562 -0.0786 0.5821 0.2161
3.000 0.7512 0.01569 0.00573 -0.0783 0.5723 0.2763
3.500 0.8049 0.01478 0.00600 -0.0775 0.5494 1.0000
3.750 0.8311 0.01499 0.00614 -0.0770 0.5372 1.0000
4.000 0.8571 0.01519 0.00629 -0.0765 0.5237 1.0000
4.250 0.8830 0.01539 0.00648 -0.0759 0.5092 1.0000
4.500 0.9087 0.01560 0.00667 -0.0753 0.4940 1.0000
4.750 0.9344 0.01584 0.00690 -0.0748 0.4789 1.0000
5.000 0.9599 0.01609 0.00718 -0.0742 0.4644 1.0000
5.250 0.9853 0.01637 0.00747 -0.0737 0.4491 1.0000
5.500 1.0105 0.01665 0.00778 -0.0731 0.4326 1.0000
5.750 1.0355 0.01697 0.00813 -0.0725 0.4159 1.0000
6.000 1.0603 0.01731 0.00854 -0.0720 0.4001 1.0000
6.250 1.0848 0.01768 0.00895 -0.0713 0.3830 1.0000
6.500 1.1090 0.01808 0.00939 -0.0707 0.3654 1.0000
6.750 1.1331 0.01852 0.00989 -0.0700 0.3492 1.0000
7.000 1.1569 0.01898 0.01048 -0.0694 0.3319 1.0000
7.250 1.1803 0.01949 0.01108 -0.0687 0.3123 1.0000
7.500 1.2021 0.02010 0.01170 -0.0679 0.2838 1.0000
7.750 1.2213 0.02095 0.01239 -0.0669 0.2385 1.0000
8.000 1.2379 0.02216 0.01330 -0.0658 0.1855 1.0000
8.250 1.2541 0.02351 0.01446 -0.0647 0.1423 1.0000
8.750 1.2822 0.02666 0.01724 -0.0622 0.0818 1.0000
9.000 1.2966 0.02815 0.01877 -0.0608 0.0553 1.0000
9.250 1.3074 0.02992 0.02040 -0.0592 0.0402 1.0000
9.500 1.3159 0.03180 0.02226 -0.0574 0.0343 1.0000
9.750 1.3242 0.03354 0.02423 -0.0556 0.0314 1.0000
10.000 1.3291 0.03544 0.02627 -0.0535 0.0294 1.0000
10.250 1.3282 0.03762 0.02856 -0.0512 0.0278 1.0000
10.500 1.3280 0.03990 0.03097 -0.0494 0.0265 1.0000
10.750 1.3297 0.04216 0.03343 -0.0480 0.0252 1.0000
11.000 1.3305 0.04467 0.03611 -0.0469 0.0240 1.0000
11.250 1.3307 0.04739 0.03898 -0.0461 0.0232 1.0000
11.500 1.3307 0.05025 0.04198 -0.0454 0.0225 1.0000
11.750 1.3307 0.05319 0.04505 -0.0449 0.0219 1.0000
12.000 1.3306 0.05622 0.04820 -0.0443 0.0213 1.0000
12.250 1.3302 0.05936 0.05145 -0.0438 0.0208 1.0000
12.500 1.3292 0.06265 0.05485 -0.0433 0.0202 1.0000
12.750 1.3280 0.06614 0.05845 -0.0425 0.0196 1.0000
13.000 1.3258 0.06976 0.06236 -0.0428 0.0192 1.0000
13.250 1.3219 0.07372 0.06657 -0.0433 0.0188 1.0000
13.500 1.3161 0.07801 0.07110 -0.0441 0.0184 1.0000
13.750 1.3085 0.08268 0.07600 -0.0453 0.0181 1.0000
14.000 1.2991 0.08776 0.08131 -0.0468 0.0179 1.0000
14.250 1.2880 0.09325 0.08703 -0.0487 0.0178 1.0000
14.500 1.2752 0.09927 0.09327 -0.0512 0.0177 1.0000
14.750 1.2612 0.10584 0.10007 -0.0544 0.0177 1.0000
15.000 1.2460 0.11301 0.10744 -0.0581 0.0177 1.0000
15.250 1.2297 0.12084 0.11548 -0.0625 0.0178 1.0000
15.500 1.2122 0.12949 0.12432 -0.0677 0.0179 1.0000
15.750 1.1937 0.13899 0.13400 -0.0737 0.0180 1.0000
16.000 1.1738 0.14962 0.14479 -0.0804 0.0183 1.0000
16.250 1.1532 0.16148 0.15672 -0.0879 0.0186 1.0000
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Polar data table (+)
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