GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 100,000 Max Cl/Cd: 31.84 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe780-il-100000-n5.txt Download as CSV file: xf-goe780-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4800 0.09170 0.08703 -0.0548 1.0000 0.0198
-10.000 -0.4882 0.08650 0.08189 -0.0574 1.0000 0.0194
-9.750 -0.4980 0.08209 0.07751 -0.0593 1.0000 0.0191
-9.500 -0.5116 0.07822 0.07366 -0.0598 1.0000 0.0189
-9.250 -0.5251 0.07544 0.07088 -0.0588 1.0000 0.0187
-9.000 -0.5476 0.07275 0.06823 -0.0558 1.0000 0.0185
-8.750 -0.5683 0.07102 0.06652 -0.0518 0.9961 0.0184
-8.500 -0.5711 0.06686 0.06219 -0.0525 0.9813 0.0180
-8.250 -0.5705 0.06229 0.05740 -0.0529 0.9699 0.0176
-8.000 -0.5672 0.05814 0.05298 -0.0526 0.9606 0.0171
-7.750 -0.5613 0.05383 0.04835 -0.0519 0.9533 0.0166
-7.500 -0.5572 0.05006 0.04425 -0.0498 0.9439 0.0164
-7.250 -0.5483 0.04653 0.04034 -0.0480 0.9368 0.0160
-7.000 -0.5399 0.04299 0.03636 -0.0453 0.9293 0.0163
-6.750 -0.5281 0.04009 0.03303 -0.0430 0.9229 0.0167
-6.500 -0.5149 0.03733 0.02974 -0.0405 0.9167 0.0176
-6.250 -0.4953 0.03431 0.02617 -0.0389 0.9129 0.0182
-6.000 -0.4781 0.03185 0.02324 -0.0366 0.9068 0.0183
-5.750 -0.4498 0.02899 0.01986 -0.0362 0.9032 0.0190
-5.500 -0.4138 0.02649 0.01694 -0.0374 0.9009 0.0198
-5.250 -0.3786 0.02442 0.01469 -0.0392 0.8990 0.0235
-5.000 -0.3513 0.02301 0.01314 -0.0392 0.8949 0.0269
-4.750 -0.3279 0.02177 0.01171 -0.0383 0.8910 0.0316
-4.500 -0.3071 0.02071 0.01053 -0.0372 0.8874 0.0413
-4.250 -0.2888 0.01959 0.00934 -0.0356 0.8837 0.0610
-4.000 -0.2718 0.01889 0.00883 -0.0338 0.8787 0.1030
-3.750 -0.1739 0.01656 0.00936 -0.0466 0.8855 0.7713
-3.500 -0.1517 0.01728 0.00989 -0.0444 0.8812 0.8206
-3.250 -0.1286 0.01780 0.01019 -0.0429 0.8772 0.8467
-3.000 -0.0893 0.01858 0.01069 -0.0442 0.8752 0.8706
-2.750 -0.0311 0.01945 0.01132 -0.0493 0.8747 0.8922
-2.500 0.0049 0.01959 0.01128 -0.0511 0.8724 0.9027
-2.250 0.0407 0.01964 0.01116 -0.0531 0.8694 0.9100
-2.000 0.0698 0.01969 0.01110 -0.0539 0.8657 0.9169
-1.750 0.1036 0.01966 0.01098 -0.0557 0.8629 0.9222
-1.500 0.1289 0.01964 0.01087 -0.0557 0.8598 0.9285
-1.250 0.1639 0.01952 0.01068 -0.0578 0.8575 0.9315
-1.000 0.1910 0.01956 0.01069 -0.0585 0.8535 0.9363
-0.750 0.2144 0.01962 0.01075 -0.0582 0.8499 0.9421
-0.500 0.2480 0.01953 0.01065 -0.0601 0.8473 0.9450
-0.250 0.2798 0.01946 0.01060 -0.0615 0.8450 0.9488
0.000 0.3021 0.01961 0.01080 -0.0611 0.8412 0.9545
0.250 0.3320 0.01962 0.01089 -0.0623 0.8379 0.9578
0.500 0.3625 0.01962 0.01096 -0.0636 0.8349 0.9614
0.750 0.3905 0.01966 0.01110 -0.0642 0.8323 0.9658
1.000 0.4207 0.01967 0.01127 -0.0653 0.8299 0.9692
1.250 0.4475 0.01969 0.01145 -0.0657 0.8230 0.9729
1.500 0.4782 0.01946 0.01135 -0.0663 0.8162 0.9762
1.750 0.5052 0.01931 0.01143 -0.0662 0.8057 0.9798
2.000 0.5272 0.01774 0.00974 -0.0619 0.7480 0.9831
2.250 0.5483 0.01722 0.00935 -0.0598 0.7035 0.9874
2.500 0.5339 0.01946 0.00884 -0.0513 0.1291 0.9932
2.750 0.5524 0.02056 0.00950 -0.0501 0.0354 0.9968
3.000 0.5773 0.02112 0.01021 -0.0499 0.0273 0.9999
3.250 0.5898 0.02179 0.01103 -0.0471 0.0237 1.0000
3.500 0.6008 0.02254 0.01197 -0.0440 0.0223 1.0000
3.750 0.6108 0.02337 0.01294 -0.0408 0.0215 1.0000
4.000 0.6207 0.02435 0.01401 -0.0375 0.0208 1.0000
4.250 0.6334 0.02549 0.01521 -0.0347 0.0195 1.0000
4.500 0.6520 0.02704 0.01677 -0.0330 0.0178 1.0000
4.750 0.6804 0.02931 0.01920 -0.0327 0.0167 1.0000
5.000 0.7067 0.03114 0.02125 -0.0321 0.0166 1.0000
5.250 0.7325 0.03350 0.02393 -0.0310 0.0166 1.0000
5.500 0.7543 0.03622 0.02695 -0.0296 0.0169 1.0000
5.750 0.7726 0.03824 0.02931 -0.0275 0.0173 1.0000
6.000 0.7911 0.03979 0.03126 -0.0248 0.0184 1.0000
6.250 0.8068 0.04280 0.03480 -0.0213 0.0202 1.0000
6.500 0.8163 0.04566 0.03803 -0.0177 0.0207 1.0000
6.750 0.8235 0.04851 0.04120 -0.0140 0.0220 1.0000
7.000 0.8273 0.05119 0.04417 -0.0101 0.0218 1.0000
7.250 0.8286 0.05401 0.04727 -0.0059 0.0222 1.0000
7.500 0.8277 0.05691 0.05040 -0.0018 0.0233 1.0000
7.750 0.8252 0.05990 0.05361 0.0020 0.0246 1.0000
11.250 0.6110 0.10808 0.10308 0.0369 0.0479 1.0000
11.750 0.5081 0.10867 0.10401 0.0427 0.0553 1.0000
12.000 0.4950 0.11365 0.10896 0.0398 0.0552 1.0000
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Polar data table (+)
Polar graphs
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