GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il) Reynolds number: 100,000 Max Cl/Cd: 59.48 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe311-il-100000-n5.txt Download as CSV file: xf-goe311-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 311 (MVA H.43) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2603 0.10357 0.09910 -0.0315 1.0000 0.0411
-8.250 -0.2592 0.10061 0.09621 -0.0322 1.0000 0.0393
-8.000 -0.2785 0.09720 0.09292 -0.0330 1.0000 0.0293
-7.750 -0.2654 0.09382 0.08955 -0.0342 0.9939 0.0287
-7.500 -0.2487 0.08968 0.08541 -0.0388 0.9816 0.0281
-7.250 -0.2304 0.08525 0.08099 -0.0445 0.9696 0.0276
-7.000 -0.2119 0.08083 0.07654 -0.0502 0.9574 0.0272
-6.750 -0.1937 0.07645 0.07214 -0.0557 0.9444 0.0274
-6.500 -0.1753 0.07188 0.06752 -0.0615 0.9303 0.0283
-6.250 -0.1563 0.06673 0.06230 -0.0676 0.9155 0.0290
-6.000 -0.1363 0.06128 0.05674 -0.0731 0.9009 0.0294
-5.750 -0.1164 0.05795 0.05333 -0.0754 0.8868 0.0300
-5.500 -0.0952 0.05476 0.05002 -0.0777 0.8727 0.0309
-5.250 -0.0717 0.05087 0.04598 -0.0807 0.8587 0.0324
-5.000 -0.0414 0.04225 0.03693 -0.0876 0.8464 0.0362
-4.750 -0.0185 0.04157 0.03617 -0.0874 0.8323 0.0390
-4.500 0.0127 0.03144 0.02525 -0.0928 0.8211 0.0461
-4.250 0.0406 0.02662 0.01961 -0.0945 0.8087 0.0565
-4.000 0.0650 0.02848 0.02170 -0.0933 0.7942 0.0615
-3.750 0.0916 0.02739 0.02026 -0.0934 0.7807 0.0712
-3.500 0.1183 0.02638 0.01892 -0.0932 0.7673 0.0774
-3.250 0.1467 0.02302 0.01475 -0.0937 0.7553 0.0793
-3.000 0.1740 0.02152 0.01280 -0.0935 0.7430 0.0807
-2.750 0.2010 0.02084 0.01187 -0.0932 0.7302 0.0822
-2.500 0.2281 0.02040 0.01123 -0.0930 0.7178 0.0848
-2.250 0.2557 0.01977 0.01033 -0.0928 0.7061 0.0882
-2.000 0.2834 0.01900 0.00924 -0.0925 0.6952 0.0907
-1.750 0.3108 0.01847 0.00851 -0.0923 0.6845 0.0929
-1.500 0.3382 0.01821 0.00818 -0.0921 0.6736 0.0958
-1.250 0.3658 0.01792 0.00775 -0.0919 0.6646 0.1005
-1.000 0.3934 0.01763 0.00733 -0.0917 0.6558 0.1072
-0.750 0.4210 0.01749 0.00711 -0.0916 0.6472 0.1175
-0.500 0.4485 0.01746 0.00697 -0.0914 0.6397 0.1315
-0.250 0.4761 0.01749 0.00691 -0.0913 0.6320 0.1464
0.000 0.5034 0.01749 0.00683 -0.0912 0.6256 0.1589
0.250 0.5308 0.01749 0.00678 -0.0911 0.6189 0.1692
0.500 0.5582 0.01750 0.00667 -0.0909 0.6127 0.1778
0.750 0.5855 0.01750 0.00664 -0.0907 0.6074 0.1845
1.000 0.6129 0.01756 0.00664 -0.0907 0.6014 0.1927
1.250 0.6400 0.01762 0.00671 -0.0905 0.5963 0.2046
1.500 0.6670 0.01771 0.00681 -0.0904 0.5911 0.2170
1.750 0.6940 0.01778 0.00687 -0.0903 0.5858 0.2250
2.000 0.7208 0.01782 0.00688 -0.0901 0.5811 0.2303
2.250 0.7477 0.01792 0.00697 -0.0900 0.5761 0.2374
2.500 0.7743 0.01801 0.00711 -0.0898 0.5708 0.2458
2.750 0.8012 0.01811 0.00720 -0.0897 0.5663 0.2593
3.000 0.8278 0.01823 0.00740 -0.0896 0.5613 0.2805
3.250 0.8541 0.01830 0.00763 -0.0895 0.5560 0.3199
3.750 0.9125 0.01754 0.00799 -0.0900 0.5459 1.0000
4.000 0.9385 0.01784 0.00828 -0.0898 0.5401 1.0000
4.250 0.9651 0.01811 0.00845 -0.0895 0.5348 1.0000
4.500 0.9896 0.01840 0.00880 -0.0890 0.5262 1.0000
4.750 1.0151 0.01863 0.00898 -0.0885 0.5174 1.0000
5.000 1.0396 0.01886 0.00923 -0.0880 0.5071 1.0000
5.250 1.0639 0.01911 0.00953 -0.0874 0.4973 1.0000
5.500 1.0893 0.01934 0.00971 -0.0869 0.4890 1.0000
5.750 1.1127 0.01962 0.01017 -0.0863 0.4794 1.0000
6.000 1.1375 0.01988 0.01048 -0.0858 0.4718 1.0000
6.250 1.1612 0.02017 0.01092 -0.0853 0.4632 1.0000
6.500 1.1854 0.02045 0.01134 -0.0848 0.4559 1.0000
6.750 1.2090 0.02075 0.01180 -0.0842 0.4474 1.0000
7.000 1.2322 0.02106 0.01227 -0.0835 0.4386 1.0000
7.250 1.2555 0.02132 0.01266 -0.0829 0.4296 1.0000
7.500 1.2774 0.02164 0.01318 -0.0820 0.4175 1.0000
7.750 1.2971 0.02183 0.01353 -0.0808 0.3966 1.0000
8.000 1.3140 0.02209 0.01376 -0.0791 0.3638 1.0000
8.250 1.3292 0.02263 0.01418 -0.0772 0.3310 1.0000
8.500 1.3417 0.02345 0.01486 -0.0751 0.2989 1.0000
8.750 1.3498 0.02460 0.01584 -0.0726 0.2611 1.0000
9.000 1.3532 0.02607 0.01710 -0.0697 0.2233 1.0000
9.250 1.3541 0.02763 0.01851 -0.0665 0.1906 1.0000
9.500 1.3510 0.02940 0.02015 -0.0630 0.1583 1.0000
9.750 1.3371 0.03217 0.02253 -0.0592 0.0981 1.0000
10.000 1.3259 0.03510 0.02523 -0.0563 0.0796 1.0000
10.250 1.3265 0.03728 0.02751 -0.0544 0.0514 1.0000
10.500 1.3139 0.04083 0.03087 -0.0525 0.0322 1.0000
10.750 1.3093 0.04386 0.03393 -0.0512 0.0278 1.0000
11.000 1.3067 0.04683 0.03705 -0.0503 0.0253 1.0000
11.250 1.3030 0.05005 0.04041 -0.0496 0.0237 1.0000
11.500 1.2982 0.05349 0.04402 -0.0491 0.0226 1.0000
11.750 1.2920 0.05723 0.04792 -0.0488 0.0218 1.0000
12.000 1.2844 0.06124 0.05211 -0.0488 0.0211 1.0000
12.250 1.2778 0.06523 0.05627 -0.0489 0.0207 1.0000
12.500 1.2725 0.06916 0.06038 -0.0491 0.0203 1.0000
12.750 1.2669 0.07319 0.06460 -0.0494 0.0197 1.0000
13.000 1.2611 0.07731 0.06889 -0.0498 0.0192 1.0000
13.250 1.2556 0.08147 0.07321 -0.0503 0.0186 1.0000
13.500 1.2504 0.08560 0.07750 -0.0508 0.0180 1.0000
13.750 1.2459 0.08966 0.08170 -0.0513 0.0175 1.0000
14.000 1.2426 0.09352 0.08569 -0.0517 0.0170 1.0000
14.250 1.2410 0.09708 0.08937 -0.0519 0.0167 1.0000
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Polar data table (+)
Polar graphs
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