GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 200,000 Max Cl/Cd: 72.78 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe346-il-200000-n5.txt Download as CSV file: xf-goe346-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3314 0.10673 0.10325 -0.0213 1.0000 0.0221
-9.500 -0.3313 0.10370 0.10024 -0.0228 1.0000 0.0221
-9.250 -0.3310 0.10052 0.09709 -0.0244 1.0000 0.0222
-9.000 -0.3292 0.09707 0.09366 -0.0256 1.0000 0.0222
-8.750 -0.3154 0.09093 0.08752 -0.0230 1.0000 0.0228
-8.500 -0.3102 0.08744 0.08405 -0.0229 1.0000 0.0232
-8.250 -0.3068 0.08419 0.08081 -0.0233 1.0000 0.0236
-8.000 -0.3042 0.08103 0.07767 -0.0237 1.0000 0.0241
-7.750 -0.3026 0.07797 0.07465 -0.0241 1.0000 0.0248
-7.500 -0.3028 0.07511 0.07184 -0.0242 1.0000 0.0256
-7.250 -0.3069 0.07275 0.06953 -0.0237 1.0000 0.0269
-7.000 -0.3163 0.07122 0.06809 -0.0231 1.0000 0.0282
-6.750 -0.3177 0.06916 0.06605 -0.0270 0.9983 0.0289
-6.500 -0.2950 0.06418 0.06099 -0.0358 0.9929 0.0292
-6.250 -0.2724 0.05909 0.05581 -0.0420 0.9881 0.0293
-6.000 -0.2485 0.05404 0.05066 -0.0475 0.9839 0.0294
-5.750 -0.2231 0.04936 0.04585 -0.0524 0.9792 0.0295
-5.500 -0.2104 0.04237 0.03887 -0.0547 0.9762 0.0303
-5.250 -0.1921 0.03854 0.03502 -0.0561 0.9713 0.0312
-5.000 -0.1679 0.03486 0.03127 -0.0590 0.9667 0.0323
-4.750 -0.1393 0.03119 0.02749 -0.0628 0.9630 0.0340
-4.500 -0.0986 0.02908 0.02503 -0.0677 0.9563 0.0397
-4.250 -0.0633 0.02597 0.02161 -0.0711 0.9513 0.0401
-4.000 -0.0352 0.02305 0.01846 -0.0728 0.9437 0.0402
-3.750 -0.0055 0.02020 0.01538 -0.0745 0.9374 0.0403
-3.500 0.0141 0.01582 0.01101 -0.0764 0.9314 0.0417
-3.250 0.0380 0.01399 0.00916 -0.0773 0.9245 0.0438
-3.000 0.0661 0.01233 0.00733 -0.0783 0.9187 0.0465
-2.750 0.0997 0.01193 0.00645 -0.0783 0.9107 0.0517
-2.500 0.1285 0.01063 0.00487 -0.0786 0.9045 0.0520
-2.000 0.1825 0.02222 0.01598 -0.0838 0.9121 0.0472
-1.750 0.2045 0.00640 0.00030 -0.0798 0.8832 0.0554
-1.250 0.2734 0.01859 0.01147 -0.0834 0.8909 0.0399
-1.000 0.3005 0.01724 0.00998 -0.0832 0.8817 0.0391
-0.750 0.3285 0.01627 0.00887 -0.0830 0.8739 0.0388
-0.500 0.3558 0.01548 0.00793 -0.0826 0.8639 0.0387
-0.250 0.3827 0.01479 0.00712 -0.0821 0.8512 0.0389
0.000 0.4091 0.01421 0.00641 -0.0813 0.8359 0.0392
0.250 0.4354 0.01374 0.00583 -0.0806 0.8193 0.0396
0.500 0.4613 0.01315 0.00516 -0.0799 0.8000 0.0416
0.750 0.4872 0.01268 0.00466 -0.0792 0.7786 0.0429
1.000 0.5133 0.01233 0.00423 -0.0785 0.7584 0.0429
1.250 0.5399 0.01203 0.00390 -0.0780 0.7415 0.0430
1.500 0.5665 0.01179 0.00365 -0.0776 0.7242 0.0433
1.750 0.5930 0.01161 0.00344 -0.0772 0.7051 0.0439
2.000 0.6195 0.01150 0.00328 -0.0767 0.6846 0.0449
2.250 0.6461 0.01143 0.00318 -0.0764 0.6624 0.0463
2.500 0.6725 0.01143 0.00311 -0.0759 0.6382 0.0484
2.750 0.6986 0.01150 0.00306 -0.0755 0.6096 0.0508
3.000 0.7237 0.01164 0.00304 -0.0748 0.5689 0.0578
3.250 0.7478 0.01193 0.00311 -0.0740 0.5191 0.0677
3.500 0.7686 0.01056 0.00331 -0.0726 0.4693 1.0000
3.750 0.7928 0.01101 0.00348 -0.0719 0.4188 1.0000
4.000 0.8167 0.01151 0.00371 -0.0713 0.3709 1.0000
4.250 0.8405 0.01204 0.00401 -0.0707 0.3275 1.0000
4.500 0.8645 0.01256 0.00433 -0.0702 0.2903 1.0000
4.750 0.8887 0.01305 0.00467 -0.0697 0.2587 1.0000
5.000 0.9129 0.01355 0.00503 -0.0693 0.2285 1.0000
5.250 0.9373 0.01400 0.00539 -0.0688 0.2068 1.0000
5.500 0.9622 0.01440 0.00576 -0.0684 0.1907 1.0000
5.750 0.9868 0.01482 0.00616 -0.0680 0.1751 1.0000
6.000 1.0113 0.01526 0.00660 -0.0675 0.1579 1.0000
6.250 1.0347 0.01583 0.00706 -0.0669 0.1255 1.0000
6.500 1.0552 0.01683 0.00773 -0.0661 0.0749 1.0000
6.750 1.0765 0.01774 0.00850 -0.0652 0.0514 1.0000
7.000 1.0987 0.01850 0.00928 -0.0644 0.0442 1.0000
7.250 1.1203 0.01931 0.01012 -0.0636 0.0397 1.0000
7.500 1.1415 0.02014 0.01106 -0.0627 0.0366 1.0000
7.750 1.1628 0.02091 0.01197 -0.0617 0.0338 1.0000
8.000 1.1825 0.02185 0.01304 -0.0607 0.0313 1.0000
8.250 1.1984 0.02323 0.01449 -0.0591 0.0286 1.0000
8.500 1.2172 0.02422 0.01561 -0.0579 0.0267 1.0000
8.750 1.2355 0.02525 0.01678 -0.0566 0.0249 1.0000
9.000 1.2528 0.02636 0.01801 -0.0552 0.0230 1.0000
9.250 1.2689 0.02752 0.01923 -0.0539 0.0213 1.0000
9.500 1.2813 0.02921 0.02100 -0.0520 0.0198 1.0000
9.750 1.2976 0.03040 0.02238 -0.0505 0.0188 1.0000
10.000 1.3119 0.03185 0.02401 -0.0488 0.0177 1.0000
10.250 1.3252 0.03330 0.02562 -0.0471 0.0167 1.0000
10.500 1.3375 0.03458 0.02703 -0.0454 0.0158 1.0000
10.750 1.3467 0.03580 0.02834 -0.0433 0.0150 1.0000
11.000 1.3516 0.03756 0.03022 -0.0409 0.0143 1.0000
11.250 1.3570 0.03951 0.03239 -0.0385 0.0138 1.0000
11.500 1.3604 0.04171 0.03485 -0.0362 0.0134 1.0000
11.750 1.3614 0.04415 0.03754 -0.0339 0.0130 1.0000
12.000 1.3598 0.04683 0.04048 -0.0318 0.0126 1.0000
12.250 1.3559 0.04977 0.04368 -0.0301 0.0123 1.0000
12.500 1.3498 0.05302 0.04718 -0.0287 0.0121 1.0000
12.750 1.3418 0.05658 0.05098 -0.0278 0.0119 1.0000
13.000 1.3323 0.06051 0.05514 -0.0276 0.0117 1.0000
13.250 1.3215 0.06484 0.05970 -0.0281 0.0115 1.0000
13.500 1.3086 0.06979 0.06487 -0.0294 0.0114 1.0000
13.750 1.2949 0.07520 0.07048 -0.0314 0.0113 1.0000
14.000 1.2776 0.08173 0.07723 -0.0344 0.0113 1.0000
14.250 1.2577 0.08927 0.08499 -0.0384 0.0113 1.0000
14.500 1.2342 0.09818 0.09413 -0.0436 0.0114 1.0000
14.750 1.2067 0.10893 0.10511 -0.0503 0.0116 1.0000
15.000 1.1740 0.12201 0.11840 -0.0585 0.0119 1.0000
15.250 1.1358 0.13796 0.13453 -0.0684 0.0124 1.0000
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Polar data table (+)
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