GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Reynolds number: 500,000 Max Cl/Cd: 81.42 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe116-il-500000-n5.txt Download as CSV file: xf-goe116-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 116 (MVA MK.3) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4008 0.09408 0.09201 -0.0315 0.9601 0.0051
-9.250 -0.3939 0.09087 0.08870 -0.0329 0.9063 0.0047
-9.000 -0.3959 0.08697 0.08466 -0.0340 0.8668 0.0046
-8.500 -0.3984 0.07780 0.07533 -0.0386 0.8260 0.0043
-8.250 -0.4018 0.07218 0.06967 -0.0421 0.8121 0.0042
-8.000 -0.4064 0.06499 0.06243 -0.0487 0.8004 0.0041
-7.750 -0.4046 0.05368 0.05100 -0.0632 0.7903 0.0040
-7.500 -0.3884 0.03738 0.03418 -0.0830 0.7823 0.0038
-7.250 -0.3700 0.03108 0.02731 -0.0882 0.7743 0.0037
-7.000 -0.3493 0.02704 0.02277 -0.0902 0.7673 0.0036
-6.750 -0.3265 0.02398 0.01925 -0.0911 0.7605 0.0037
-6.500 -0.3021 0.02157 0.01644 -0.0916 0.7543 0.0037
-6.250 -0.2766 0.01962 0.01414 -0.0918 0.7478 0.0039
-6.000 -0.2505 0.01799 0.01220 -0.0919 0.7419 0.0041
-5.750 -0.2237 0.01666 0.01060 -0.0920 0.7356 0.0044
-5.500 -0.1961 0.01590 0.00961 -0.0920 0.7300 0.0048
-5.250 -0.1696 0.01471 0.00829 -0.0923 0.7247 0.0054
-5.000 -0.1421 0.01393 0.00738 -0.0924 0.7193 0.0058
-4.750 -0.1144 0.01317 0.00647 -0.0925 0.7142 0.0060
-4.500 -0.0863 0.01250 0.00568 -0.0927 0.7089 0.0064
-4.250 -0.0581 0.01194 0.00499 -0.0929 0.7039 0.0069
-4.000 -0.0297 0.01150 0.00440 -0.0930 0.6993 0.0076
-3.750 -0.0013 0.01093 0.00368 -0.0932 0.6944 0.0090
-3.500 0.0272 0.01056 0.00314 -0.0934 0.6897 0.0106
-3.250 0.0557 0.01032 0.00275 -0.0935 0.6854 0.0124
-3.000 0.0844 0.01014 0.00246 -0.0937 0.6808 0.0150
-2.750 0.1129 0.00993 0.00221 -0.0938 0.6761 0.0243
-2.500 0.1406 0.00952 0.00214 -0.0941 0.6721 0.1320
-2.250 0.1693 0.00956 0.00219 -0.0944 0.6676 0.1395
-2.000 0.1981 0.00976 0.00232 -0.0945 0.6631 0.1465
-1.750 0.2264 0.00968 0.00223 -0.0947 0.6590 0.1508
-1.500 0.2549 0.00960 0.00212 -0.0949 0.6547 0.1518
-1.250 0.2834 0.00954 0.00203 -0.0952 0.6502 0.1528
-1.000 0.3118 0.00949 0.00195 -0.0953 0.6462 0.1538
-0.750 0.3402 0.00945 0.00188 -0.0955 0.6424 0.1549
-0.500 0.3687 0.00940 0.00183 -0.0958 0.6384 0.1560
-0.250 0.3972 0.00937 0.00179 -0.0960 0.6343 0.1572
0.000 0.4255 0.00936 0.00176 -0.0962 0.6308 0.1585
0.250 0.4540 0.00934 0.00175 -0.0964 0.6271 0.1597
0.500 0.4825 0.00932 0.00175 -0.0966 0.6231 0.1605
0.750 0.5109 0.00929 0.00174 -0.0968 0.6193 0.1621
1.000 0.5392 0.00927 0.00174 -0.0970 0.6158 0.1638
1.250 0.5676 0.00924 0.00177 -0.0972 0.6106 0.1655
1.500 0.5958 0.00924 0.00180 -0.0974 0.6044 0.1674
1.750 0.6240 0.00925 0.00184 -0.0976 0.5988 0.1694
2.000 0.6523 0.00926 0.00190 -0.0977 0.5933 0.1716
2.250 0.6803 0.00930 0.00196 -0.0979 0.5868 0.1737
2.500 0.7085 0.00930 0.00204 -0.0980 0.5789 0.1763
2.750 0.7364 0.00932 0.00212 -0.0981 0.5712 0.1801
3.000 0.7637 0.00938 0.00220 -0.0981 0.5492 0.1845
3.500 0.8133 0.01005 0.00251 -0.0974 0.4375 0.1979
3.750 0.8234 0.01237 0.00363 -0.0954 0.1874 0.2072
4.000 0.8384 0.01401 0.00460 -0.0938 0.0193 0.2280
4.250 0.8591 0.01272 0.00511 -0.0928 0.0140 1.0000
4.500 0.8837 0.01317 0.00561 -0.0923 0.0100 1.0000
4.750 0.9074 0.01373 0.00627 -0.0916 0.0085 1.0000
5.000 0.9308 0.01427 0.00688 -0.0910 0.0077 1.0000
5.250 0.9539 0.01481 0.00746 -0.0903 0.0067 1.0000
5.500 0.9761 0.01540 0.00809 -0.0896 0.0057 1.0000
5.750 0.9944 0.01639 0.00917 -0.0881 0.0052 1.0000
6.000 1.0136 0.01723 0.01009 -0.0868 0.0049 1.0000
6.250 1.0308 0.01823 0.01117 -0.0851 0.0046 1.0000
6.500 1.0464 0.01934 0.01236 -0.0832 0.0044 1.0000
6.750 1.0612 0.02055 0.01364 -0.0812 0.0042 1.0000
7.000 1.0760 0.02185 0.01502 -0.0791 0.0041 1.0000
7.250 1.0928 0.02297 0.01620 -0.0776 0.0038 1.0000
7.500 1.1105 0.02380 0.01711 -0.0763 0.0035 1.0000
7.750 1.1260 0.02536 0.01874 -0.0747 0.0032 1.0000
8.000 1.1460 0.02683 0.02038 -0.0733 0.0030 1.0000
8.250 1.1692 0.02916 0.02292 -0.0723 0.0028 1.0000
8.500 1.1930 0.03200 0.02600 -0.0713 0.0026 1.0000
8.750 1.2127 0.03501 0.02929 -0.0699 0.0025 1.0000
9.000 1.2282 0.03827 0.03285 -0.0679 0.0024 1.0000
9.250 1.2385 0.04169 0.03658 -0.0655 0.0025 1.0000
9.500 1.2444 0.04522 0.04041 -0.0626 0.0025 1.0000
9.750 1.2452 0.04871 0.04420 -0.0594 0.0025 1.0000
10.000 1.2403 0.05198 0.04772 -0.0557 0.0026 1.0000
10.250 1.2306 0.05503 0.05099 -0.0518 0.0026 1.0000
10.500 1.2183 0.05823 0.05440 -0.0484 0.0027 1.0000
10.750 1.2043 0.06166 0.05802 -0.0457 0.0027 1.0000
11.000 1.1890 0.06541 0.06197 -0.0437 0.0027 1.0000
11.250 1.1730 0.06945 0.06618 -0.0425 0.0028 1.0000
11.500 1.1556 0.07389 0.07079 -0.0419 0.0028 1.0000
11.750 1.1378 0.07866 0.07572 -0.0420 0.0028 1.0000
12.000 1.1190 0.08393 0.08115 -0.0429 0.0029 1.0000
12.250 1.1001 0.08952 0.08688 -0.0444 0.0029 1.0000
12.500 1.0808 0.09568 0.09317 -0.0466 0.0029 1.0000
12.750 1.0611 0.10242 0.10004 -0.0497 0.0029 1.0000
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Polar data table (+)
Polar graphs
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