GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 50,000 Max Cl/Cd: 31.58 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe11k-il-50000-n5.txt Download as CSV file: xf-goe11k-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 11K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4716 0.10596 0.09897 -0.0315 1.0000 0.0578
-8.500 -0.4738 0.10278 0.09584 -0.0309 1.0000 0.0559
-7.500 -0.5214 0.08856 0.08200 -0.0343 1.0000 0.0477
-7.250 -0.5241 0.08485 0.07830 -0.0342 1.0000 0.0476
-7.000 -0.5256 0.08112 0.07457 -0.0340 1.0000 0.0475
-6.750 -0.5267 0.07698 0.07038 -0.0343 1.0000 0.0475
-6.500 -0.5260 0.07274 0.06606 -0.0345 1.0000 0.0475
-6.250 -0.5231 0.06867 0.06189 -0.0344 1.0000 0.0474
-6.000 -0.5185 0.06439 0.05743 -0.0343 1.0000 0.0473
-5.750 -0.5121 0.05989 0.05271 -0.0342 1.0000 0.0473
-5.500 -0.5040 0.05579 0.04839 -0.0339 1.0000 0.0485
-5.250 -0.4936 0.05376 0.04632 -0.0326 1.0000 0.0512
-5.000 -0.4811 0.05018 0.04244 -0.0321 1.0000 0.0532
-4.750 -0.4666 0.04617 0.03798 -0.0316 1.0000 0.0546
-4.500 -0.4500 0.04225 0.03344 -0.0309 1.0000 0.0572
-4.250 -0.4319 0.03878 0.02929 -0.0300 1.0000 0.0610
-4.000 -0.4133 0.03669 0.02689 -0.0289 1.0000 0.0656
-3.750 -0.3926 0.03416 0.02371 -0.0277 1.0000 0.0722
-3.500 -0.3717 0.03245 0.02156 -0.0265 1.0000 0.0801
-3.250 -0.3508 0.03096 0.01984 -0.0255 1.0000 0.0877
-3.000 -0.3292 0.02965 0.01820 -0.0244 1.0000 0.0981
-2.750 -0.3064 0.02855 0.01670 -0.0233 1.0000 0.1073
-2.500 -0.2840 0.02770 0.01571 -0.0225 1.0000 0.1176
-2.250 -0.2588 0.02681 0.01444 -0.0218 1.0000 0.1236
-2.000 -0.2343 0.02608 0.01360 -0.0211 1.0000 0.1295
-1.750 -0.2093 0.02564 0.01294 -0.0207 1.0000 0.1400
-1.500 -0.1850 0.02524 0.01240 -0.0202 1.0000 0.1510
-1.250 -0.1607 0.02481 0.01187 -0.0196 1.0000 0.1594
-1.000 -0.1368 0.02445 0.01145 -0.0191 1.0000 0.1726
-0.750 -0.1126 0.02408 0.01112 -0.0187 1.0000 0.1958
-0.500 -0.0508 0.02139 0.01114 -0.0260 1.0000 1.0000
-0.250 -0.0298 0.02163 0.01100 -0.0249 1.0000 1.0000
0.000 -0.0090 0.02189 0.01097 -0.0239 1.0000 1.0000
0.250 0.0118 0.02216 0.01099 -0.0230 1.0000 1.0000
0.500 0.0325 0.02245 0.01109 -0.0220 1.0000 1.0000
0.750 0.0530 0.02277 0.01123 -0.0211 1.0000 1.0000
1.000 0.0774 0.02316 0.01148 -0.0211 0.9984 1.0000
1.250 0.1075 0.02372 0.01193 -0.0222 0.9948 1.0000
1.500 0.1367 0.02420 0.01233 -0.0232 0.9905 1.0000
1.750 0.1675 0.02483 0.01289 -0.0245 0.9866 1.0000
2.000 0.1977 0.02531 0.01335 -0.0257 0.9807 1.0000
2.250 0.2333 0.02587 0.01392 -0.0279 0.9724 1.0000
2.500 0.2734 0.02639 0.01448 -0.0309 0.9608 1.0000
2.750 0.3131 0.02682 0.01499 -0.0336 0.9489 1.0000
3.000 0.3531 0.02734 0.01561 -0.0365 0.9402 1.0000
3.250 0.3808 0.02763 0.01602 -0.0369 0.9302 1.0000
3.500 0.4142 0.02804 0.01659 -0.0385 0.9214 1.0000
3.750 0.4496 0.02841 0.01716 -0.0403 0.9119 1.0000
4.000 0.4800 0.02868 0.01767 -0.0410 0.9001 1.0000
4.250 0.5134 0.02889 0.01814 -0.0422 0.8877 1.0000
4.500 0.5638 0.02818 0.01781 -0.0451 0.8608 1.0000
4.750 0.6248 0.02493 0.01495 -0.0459 0.7885 1.0000
5.000 0.6438 0.02416 0.01446 -0.0425 0.7392 1.0000
5.250 0.6639 0.02357 0.01411 -0.0393 0.6701 1.0000
5.500 0.7357 0.02330 0.01212 -0.0426 0.3207 1.0000
5.750 0.7419 0.02515 0.01319 -0.0392 0.2161 1.0000
6.000 0.7581 0.02669 0.01441 -0.0374 0.1726 1.0000
6.250 0.7805 0.02809 0.01576 -0.0366 0.1484 1.0000
6.500 0.8066 0.02955 0.01717 -0.0365 0.1229 1.0000
6.750 0.8379 0.03118 0.01886 -0.0374 0.0966 1.0000
7.000 0.8757 0.03327 0.02109 -0.0390 0.0756 1.0000
7.250 0.9103 0.03560 0.02349 -0.0403 0.0629 1.0000
7.500 0.9431 0.03822 0.02655 -0.0408 0.0540 1.0000
7.750 0.9699 0.04117 0.02985 -0.0405 0.0491 1.0000
8.000 0.9895 0.04409 0.03331 -0.0389 0.0449 1.0000
8.250 1.0037 0.04651 0.03601 -0.0370 0.0418 1.0000
8.500 1.0161 0.04969 0.03935 -0.0351 0.0402 1.0000
8.750 1.0207 0.05323 0.04352 -0.0315 0.0393 1.0000
9.000 1.0190 0.05680 0.04765 -0.0273 0.0382 1.0000
9.250 1.0142 0.06031 0.05159 -0.0233 0.0375 1.0000
9.500 1.0056 0.06377 0.05545 -0.0192 0.0369 1.0000
9.750 0.9932 0.06711 0.05908 -0.0150 0.0365 1.0000
10.000 0.9773 0.07042 0.06262 -0.0109 0.0364 1.0000
10.250 0.9594 0.07394 0.06634 -0.0074 0.0364 1.0000
10.500 0.9406 0.07772 0.07026 -0.0049 0.0365 1.0000
10.750 0.9203 0.08198 0.07467 -0.0035 0.0368 1.0000
11.000 0.8988 0.08688 0.07969 -0.0036 0.0370 1.0000
11.250 0.8786 0.09240 0.08529 -0.0050 0.0374 1.0000
11.500 0.8616 0.09845 0.09138 -0.0077 0.0380 1.0000
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Polar data table (+)
Polar graphs
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