GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 100,000 Max Cl/Cd: 70.63 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe804-il-100000.txt Download as CSV file: xf-goe804-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 804 (EA 8) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.4090 0.10842 0.10399 -0.0138 1.0000 0.0554
-6.500 -0.4138 0.10652 0.10213 -0.0121 1.0000 0.0563
-6.250 -0.4170 0.10441 0.10007 -0.0110 1.0000 0.0574
-6.000 -0.4179 0.10213 0.09783 -0.0107 1.0000 0.0585
-5.750 -0.4176 0.09969 0.09543 -0.0111 1.0000 0.0599
-5.500 -0.4152 0.09710 0.09287 -0.0125 1.0000 0.0618
-5.250 -0.4079 0.09454 0.09033 -0.0164 1.0000 0.0637
-5.000 -0.3740 0.09193 0.08764 -0.0338 1.0000 0.0653
-4.750 -0.3648 0.08717 0.08290 -0.0351 1.0000 0.0660
-4.500 -0.3687 0.08351 0.07931 -0.0292 1.0000 0.0671
-4.250 -0.3624 0.08047 0.07629 -0.0276 1.0000 0.0689
-4.000 -0.3477 0.07736 0.07315 -0.0296 1.0000 0.0730
-3.750 -0.2904 0.07193 0.06751 -0.0477 1.0000 0.0799
-3.500 -0.2868 0.06892 0.06457 -0.0444 1.0000 0.0818
-3.250 -0.2077 0.06447 0.05964 -0.0648 1.0000 0.0928
-3.000 -0.2047 0.06046 0.05579 -0.0616 1.0000 0.0942
-2.750 -0.1437 0.05704 0.05195 -0.0739 1.0000 0.1065
-2.500 -0.1359 0.05335 0.04844 -0.0718 1.0000 0.1090
-2.250 -0.0976 0.05023 0.04516 -0.0775 1.0000 0.1230
-2.000 -0.0601 0.04738 0.04217 -0.0825 1.0000 0.1379
-1.750 -0.0235 0.04482 0.03949 -0.0868 1.0000 0.1544
-1.500 0.0181 0.04252 0.03698 -0.0922 1.0000 0.1808
-1.000 0.1461 0.03543 0.02850 -0.1087 1.0000 0.1306
-0.750 0.2012 0.03274 0.02505 -0.1141 1.0000 0.1150
-0.500 0.2424 0.03141 0.02321 -0.1170 1.0000 0.1153
-0.250 0.2764 0.03077 0.02224 -0.1187 1.0000 0.1239
0.000 0.3068 0.03047 0.02174 -0.1198 1.0000 0.1304
0.250 0.3516 0.03037 0.02151 -0.1234 0.9957 0.1427
0.500 0.4033 0.03035 0.02142 -0.1281 0.9870 0.1556
0.750 0.4497 0.03040 0.02150 -0.1320 0.9777 0.1735
1.000 0.4964 0.03040 0.02160 -0.1358 0.9695 0.2005
1.250 0.5318 0.02848 0.02168 -0.1371 0.9629 1.0000
1.500 0.5687 0.02899 0.02179 -0.1389 0.9527 1.0000
1.750 0.6066 0.02957 0.02221 -0.1412 0.9451 1.0000
2.000 0.6431 0.03003 0.02258 -0.1433 0.9364 1.0000
2.250 0.6768 0.03040 0.02291 -0.1448 0.9257 1.0000
2.500 0.7142 0.03070 0.02319 -0.1467 0.9157 1.0000
2.750 0.7606 0.03084 0.02332 -0.1501 0.9079 1.0000
3.000 0.7921 0.03102 0.02354 -0.1509 0.8964 1.0000
3.250 0.8254 0.03120 0.02380 -0.1520 0.8857 1.0000
3.500 0.8739 0.03101 0.02370 -0.1554 0.8796 1.0000
3.750 0.9061 0.03094 0.02373 -0.1560 0.8673 1.0000
4.000 0.9412 0.03070 0.02366 -0.1568 0.8552 1.0000
4.250 0.9805 0.03013 0.02324 -0.1580 0.8430 1.0000
4.500 1.0269 0.02879 0.02209 -0.1597 0.8292 1.0000
4.750 1.0822 0.02630 0.01988 -0.1615 0.8131 1.0000
5.000 1.1284 0.02425 0.01810 -0.1623 0.7980 1.0000
5.250 1.1649 0.02256 0.01666 -0.1614 0.7779 1.0000
5.500 1.1986 0.02084 0.01520 -0.1597 0.7446 1.0000
5.750 1.2713 0.01800 0.01214 -0.1634 0.6227 1.0000
6.000 1.2828 0.02001 0.01250 -0.1590 0.3801 1.0000
6.250 1.2717 0.02314 0.01424 -0.1524 0.2033 1.0000
6.500 1.2747 0.02570 0.01603 -0.1483 0.1263 1.0000
6.750 1.2824 0.02797 0.01815 -0.1448 0.1017 1.0000
7.000 1.2966 0.03001 0.02008 -0.1425 0.0849 1.0000
7.250 1.3215 0.03223 0.02227 -0.1417 0.0739 1.0000
7.500 1.3574 0.03482 0.02486 -0.1430 0.0640 1.0000
7.750 1.4095 0.03904 0.02899 -0.1471 0.0578 1.0000
8.000 1.4375 0.04177 0.03223 -0.1464 0.0543 1.0000
8.250 1.4623 0.04481 0.03573 -0.1454 0.0516 1.0000
8.500 1.4843 0.04874 0.04018 -0.1437 0.0510 1.0000
8.750 1.4998 0.05322 0.04526 -0.1412 0.0516 1.0000
9.000 1.5089 0.05799 0.05060 -0.1380 0.0526 1.0000
9.250 1.5121 0.06253 0.05564 -0.1343 0.0529 1.0000
9.500 1.5110 0.06713 0.06070 -0.1304 0.0534 1.0000
9.750 1.5055 0.07189 0.06588 -0.1263 0.0540 1.0000
10.000 1.5025 0.07791 0.07216 -0.1234 0.0558 1.0000
10.250 1.4037 0.07801 0.07295 -0.1057 0.0586 1.0000
10.500 1.3268 0.08331 0.07896 -0.0959 0.0630 1.0000
10.750 1.2920 0.08937 0.08529 -0.0928 0.0654 1.0000
11.000 1.2641 0.09527 0.09138 -0.0910 0.0670 1.0000
11.250 1.2330 0.10109 0.09738 -0.0901 0.0678 1.0000
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Polar data table (+)
Polar graphs
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