GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Reynolds number: 200,000 Max Cl/Cd: 57.61 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe235-il-200000-n5.txt Download as CSV file: xf-goe235-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 235 (SCHTTE-LANZ) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4390 0.10004 0.09632 -0.0003 1.0000 0.0331
-8.000 -0.4348 0.09690 0.09321 -0.0038 1.0000 0.0335
-7.750 -0.4310 0.09366 0.09000 -0.0088 1.0000 0.0337
-7.500 -0.4188 0.08938 0.08571 -0.0181 1.0000 0.0338
-7.250 -0.4099 0.08599 0.08237 -0.0153 1.0000 0.0341
-7.000 -0.3989 0.08286 0.07926 -0.0153 1.0000 0.0344
-6.750 -0.3862 0.07964 0.07606 -0.0174 1.0000 0.0348
-6.500 -0.3722 0.07637 0.07280 -0.0202 1.0000 0.0352
-6.250 -0.3567 0.07304 0.06947 -0.0234 1.0000 0.0358
-6.000 -0.3399 0.06966 0.06608 -0.0269 1.0000 0.0366
-5.750 -0.3218 0.06623 0.06263 -0.0306 1.0000 0.0375
-5.500 -0.2950 0.06210 0.05838 -0.0377 0.9986 0.0390
-5.250 -0.2522 0.05653 0.05255 -0.0475 0.9856 0.0395
-5.000 -0.2297 0.05337 0.04944 -0.0491 0.9755 0.0399
-4.750 -0.2022 0.05034 0.04637 -0.0519 0.9647 0.0405
-4.500 -0.1726 0.04735 0.04328 -0.0551 0.9534 0.0413
-4.250 -0.1419 0.04436 0.04017 -0.0582 0.9417 0.0424
-4.000 -0.1091 0.04130 0.03691 -0.0613 0.9292 0.0443
-3.750 -0.0679 0.03808 0.03305 -0.0646 0.9146 0.0457
-3.500 -0.0464 0.03506 0.03004 -0.0651 0.8972 0.0462
-3.250 -0.0254 0.03327 0.02824 -0.0649 0.8771 0.0472
-3.000 -0.0017 0.03162 0.02643 -0.0646 0.8577 0.0487
-2.750 0.0246 0.02977 0.02433 -0.0645 0.8402 0.0502
-2.250 0.0852 0.02419 0.01781 -0.0645 0.8142 0.0387
-2.000 0.1121 0.02267 0.01608 -0.0644 0.8025 0.0381
-1.750 0.1401 0.02121 0.01438 -0.0644 0.7895 0.0377
-1.500 0.1685 0.01994 0.01281 -0.0641 0.7745 0.0382
-1.250 0.1972 0.01889 0.01139 -0.0637 0.7584 0.0390
-1.000 0.2251 0.01785 0.01016 -0.0634 0.7417 0.0388
-0.750 0.2529 0.01694 0.00904 -0.0631 0.7231 0.0388
-0.500 0.2808 0.01616 0.00805 -0.0627 0.7030 0.0389
-0.250 0.3085 0.01551 0.00720 -0.0623 0.6844 0.0391
0.250 0.3632 0.01441 0.00581 -0.0615 0.6473 0.0401
0.500 0.3903 0.01411 0.00546 -0.0612 0.6297 0.0416
0.750 0.4175 0.01387 0.00510 -0.0608 0.6102 0.0433
1.000 0.4449 0.01357 0.00472 -0.0604 0.5889 0.0440
1.250 0.4722 0.01333 0.00439 -0.0601 0.5578 0.0448
1.500 0.4983 0.01330 0.00408 -0.0595 0.4815 0.0456
1.750 0.5225 0.01358 0.00391 -0.0591 0.3856 0.0468
2.000 0.5475 0.01398 0.00393 -0.0588 0.2937 0.0488
2.250 0.5736 0.01428 0.00399 -0.0587 0.2504 0.0520
2.500 0.6004 0.01438 0.00400 -0.0585 0.2326 0.0542
2.750 0.6273 0.01452 0.00405 -0.0584 0.2179 0.0571
3.000 0.6543 0.01466 0.00412 -0.0582 0.2060 0.0610
3.250 0.6813 0.01476 0.00422 -0.0580 0.1976 0.0699
3.500 0.7084 0.01462 0.00441 -0.0580 0.1907 0.2121
3.750 0.7313 0.01328 0.00458 -0.0569 0.1831 1.0000
4.000 0.7584 0.01351 0.00475 -0.0567 0.1744 1.0000
4.250 0.7851 0.01380 0.00496 -0.0564 0.1660 1.0000
4.500 0.8117 0.01409 0.00516 -0.0562 0.1516 1.0000
4.750 0.8358 0.01485 0.00547 -0.0558 0.0725 1.0000
5.000 0.8598 0.01569 0.00613 -0.0553 0.0490 1.0000
5.250 0.8854 0.01617 0.00658 -0.0549 0.0457 1.0000
5.500 0.9108 0.01667 0.00708 -0.0545 0.0437 1.0000
5.750 0.9360 0.01721 0.00765 -0.0541 0.0422 1.0000
6.000 0.9612 0.01771 0.00820 -0.0536 0.0413 1.0000
6.250 0.9862 0.01823 0.00878 -0.0532 0.0405 1.0000
6.500 1.0107 0.01879 0.00942 -0.0527 0.0397 1.0000
6.750 1.0348 0.01940 0.01009 -0.0522 0.0387 1.0000
7.000 1.0581 0.02007 0.01081 -0.0516 0.0377 1.0000
7.250 1.0806 0.02083 0.01161 -0.0509 0.0368 1.0000
7.500 1.1020 0.02171 0.01252 -0.0502 0.0362 1.0000
7.750 1.1221 0.02273 0.01355 -0.0493 0.0356 1.0000
8.000 1.1417 0.02382 0.01465 -0.0483 0.0351 1.0000
8.250 1.1627 0.02471 0.01559 -0.0474 0.0348 1.0000
8.500 1.1833 0.02564 0.01660 -0.0465 0.0344 1.0000
8.750 1.2036 0.02660 0.01764 -0.0456 0.0339 1.0000
9.000 1.2236 0.02761 0.01871 -0.0447 0.0332 1.0000
9.250 1.2431 0.02868 0.01986 -0.0437 0.0325 1.0000
9.500 1.2622 0.02984 0.02107 -0.0427 0.0320 1.0000
9.750 1.2811 0.03106 0.02236 -0.0417 0.0315 1.0000
10.000 1.2996 0.03235 0.02372 -0.0407 0.0311 1.0000
10.250 1.3177 0.03372 0.02516 -0.0397 0.0306 1.0000
10.500 1.3355 0.03524 0.02671 -0.0388 0.0301 1.0000
10.750 1.3543 0.03734 0.02881 -0.0382 0.0294 1.0000
11.000 1.3681 0.03873 0.03041 -0.0368 0.0290 1.0000
11.250 1.3806 0.04024 0.03215 -0.0353 0.0285 1.0000
11.500 1.3917 0.04195 0.03410 -0.0337 0.0282 1.0000
11.750 1.4004 0.04380 0.03617 -0.0320 0.0278 1.0000
12.000 1.4052 0.04567 0.03827 -0.0299 0.0273 1.0000
12.250 1.4067 0.04763 0.04042 -0.0277 0.0269 1.0000
12.500 1.4069 0.04972 0.04269 -0.0257 0.0265 1.0000
12.750 1.4064 0.05196 0.04510 -0.0242 0.0261 1.0000
13.000 1.4056 0.05435 0.04766 -0.0230 0.0257 1.0000
13.250 1.4048 0.05690 0.05033 -0.0221 0.0254 1.0000
13.500 1.4007 0.05985 0.05344 -0.0215 0.0252 1.0000
13.750 1.3953 0.06311 0.05686 -0.0213 0.0250 1.0000
14.000 1.3886 0.06671 0.06061 -0.0214 0.0248 1.0000
14.250 1.3802 0.07068 0.06474 -0.0220 0.0246 1.0000
14.500 1.3698 0.07514 0.06936 -0.0230 0.0245 1.0000
14.750 1.3570 0.08014 0.07453 -0.0245 0.0243 1.0000
15.000 1.3385 0.08607 0.08067 -0.0272 0.0243 1.0000
15.250 1.3171 0.09279 0.08761 -0.0309 0.0242 1.0000
15.500 1.2946 0.10027 0.09531 -0.0354 0.0242 1.0000
15.750 1.2716 0.10856 0.10382 -0.0408 0.0242 1.0000
16.000 1.2478 0.11779 0.11324 -0.0471 0.0242 1.0000
16.250 1.2228 0.12809 0.12372 -0.0543 0.0243 1.0000
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