GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 474 AIRFOIL (goe474-il) Reynolds number: 100,000 Max Cl/Cd: 56.97 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe474-il-100000.txt Download as CSV file: xf-goe474-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 474 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4237 0.09142 0.08648 -0.0245 1.0000 0.1047
-7.750 -0.4359 0.08947 0.08465 -0.0259 1.0000 0.1075
-7.500 -0.4560 0.08805 0.08334 -0.0341 1.0000 0.1091
-7.250 -0.4514 0.08311 0.07844 -0.0327 1.0000 0.1103
-7.000 -0.4410 0.07940 0.07478 -0.0288 1.0000 0.1120
-6.750 -0.4361 0.07643 0.07184 -0.0276 1.0000 0.1145
-6.500 -0.4343 0.07350 0.06893 -0.0280 1.0000 0.1177
-6.250 -0.4416 0.07106 0.06625 -0.0370 1.0000 0.1236
-6.000 -0.4351 0.06654 0.06191 -0.0326 1.0000 0.1251
-5.750 -0.4292 0.06402 0.05946 -0.0290 1.0000 0.1287
-5.500 -0.4235 0.06163 0.05664 -0.0346 1.0000 0.1380
-5.250 -0.4175 0.05735 0.05254 -0.0316 1.0000 0.1395
-5.000 -0.4010 0.04293 0.03709 -0.0375 1.0000 0.0832
-4.750 -0.3877 0.03984 0.03395 -0.0361 1.0000 0.0800
-4.500 -0.3725 0.03514 0.02884 -0.0356 1.0000 0.0766
-4.250 -0.3543 0.03119 0.02433 -0.0349 1.0000 0.0779
-4.000 -0.3338 0.02772 0.02020 -0.0341 1.0000 0.0802
-3.750 -0.3110 0.02477 0.01650 -0.0331 1.0000 0.0823
-3.500 -0.2909 0.02383 0.01556 -0.0321 1.0000 0.0881
-3.250 -0.2677 0.02249 0.01368 -0.0310 1.0000 0.0958
-3.000 -0.2465 0.02159 0.01281 -0.0301 1.0000 0.1031
-2.750 -0.2254 0.02100 0.01209 -0.0290 1.0000 0.1154
-2.500 -0.2037 0.02028 0.01126 -0.0280 1.0000 0.1321
-2.250 -0.1829 0.01973 0.01063 -0.0269 1.0000 0.1622
-2.000 -0.1631 0.01945 0.01033 -0.0259 1.0000 0.1887
-1.750 -0.1428 0.01920 0.01001 -0.0250 1.0000 0.2057
-1.500 -0.1229 0.01913 0.00986 -0.0241 1.0000 0.2241
-1.250 -0.1033 0.01895 0.00976 -0.0233 1.0000 0.2431
-1.000 -0.0823 0.01881 0.00956 -0.0225 0.9999 0.2547
-0.750 -0.0446 0.01875 0.00951 -0.0249 0.9946 0.2672
-0.500 -0.0095 0.01863 0.00945 -0.0269 0.9889 0.2815
-0.250 0.0282 0.01859 0.00954 -0.0292 0.9839 0.2992
0.000 0.0615 0.01848 0.00960 -0.0308 0.9776 0.3273
0.250 0.1199 0.01661 0.00969 -0.0368 0.9759 1.0000
0.500 0.1651 0.01707 0.00984 -0.0404 0.9665 1.0000
0.750 0.2177 0.01746 0.01006 -0.0454 0.9562 1.0000
1.000 0.2572 0.01767 0.01018 -0.0479 0.9446 1.0000
1.250 0.2934 0.01794 0.01038 -0.0498 0.9347 1.0000
1.500 0.3393 0.01817 0.01059 -0.0534 0.9268 1.0000
1.750 0.3762 0.01833 0.01076 -0.0552 0.9161 1.0000
2.000 0.4156 0.01840 0.01085 -0.0572 0.9044 1.0000
2.250 0.4732 0.01793 0.01045 -0.0619 0.8895 1.0000
2.500 0.5312 0.01724 0.00988 -0.0662 0.8750 1.0000
2.750 0.5727 0.01688 0.00961 -0.0678 0.8620 1.0000
3.000 0.6130 0.01638 0.00925 -0.0688 0.8470 1.0000
3.250 0.6530 0.01567 0.00864 -0.0692 0.8289 1.0000
3.500 0.6822 0.01518 0.00823 -0.0678 0.8062 1.0000
3.750 0.7123 0.01467 0.00779 -0.0664 0.7821 1.0000
4.000 0.7371 0.01435 0.00756 -0.0643 0.7529 1.0000
4.250 0.7597 0.01413 0.00738 -0.0619 0.7164 1.0000
4.500 0.7822 0.01396 0.00718 -0.0594 0.6665 1.0000
4.750 0.8004 0.01405 0.00703 -0.0561 0.5784 1.0000
5.000 0.8110 0.01499 0.00710 -0.0519 0.4333 1.0000
5.250 0.8226 0.01643 0.00785 -0.0488 0.3454 1.0000
5.500 0.8391 0.01766 0.00866 -0.0467 0.2950 1.0000
5.750 0.8587 0.01872 0.00951 -0.0452 0.2604 1.0000
6.000 0.8792 0.01974 0.01035 -0.0439 0.2346 1.0000
6.250 0.9000 0.02067 0.01123 -0.0427 0.2119 1.0000
6.500 0.9212 0.02170 0.01218 -0.0416 0.1921 1.0000
6.750 0.9417 0.02265 0.01316 -0.0404 0.1720 1.0000
7.000 0.9611 0.02378 0.01418 -0.0391 0.1512 1.0000
7.250 0.9781 0.02471 0.01518 -0.0374 0.1272 1.0000
7.500 0.9955 0.02608 0.01662 -0.0356 0.1043 1.0000
7.750 1.0132 0.02747 0.01794 -0.0341 0.0870 1.0000
8.000 1.0344 0.02950 0.02010 -0.0328 0.0756 1.0000
8.250 1.0548 0.03160 0.02234 -0.0315 0.0674 1.0000
8.500 1.0745 0.03335 0.02420 -0.0303 0.0615 1.0000
8.750 1.0943 0.03668 0.02779 -0.0291 0.0584 1.0000
9.000 1.1081 0.03960 0.03131 -0.0268 0.0559 1.0000
9.250 1.1201 0.04215 0.03423 -0.0247 0.0529 1.0000
9.500 1.1333 0.04438 0.03660 -0.0232 0.0502 1.0000
9.750 1.1404 0.04800 0.04055 -0.0210 0.0494 1.0000
10.000 1.1416 0.05215 0.04510 -0.0185 0.0491 1.0000
10.250 1.1361 0.05623 0.04965 -0.0154 0.0494 1.0000
10.500 1.1108 0.06120 0.05524 -0.0110 0.0507 1.0000
10.750 1.0749 0.06614 0.06061 -0.0068 0.0521 1.0000
11.000 1.0435 0.07112 0.06584 -0.0049 0.0531 1.0000
11.250 1.0126 0.07686 0.07177 -0.0055 0.0542 1.0000
11.500 0.9825 0.08361 0.07865 -0.0083 0.0551 1.0000
11.750 0.9523 0.09213 0.08726 -0.0135 0.0562 1.0000
12.000 0.9324 0.10064 0.09577 -0.0187 0.0576 1.0000
12.250 0.9206 0.10842 0.10353 -0.0226 0.0587 1.0000
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Polar data table (+)
Polar graphs
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