GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 200,000 Max Cl/Cd: 72.04 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe316-il-200000-n5.txt Download as CSV file: xf-goe316-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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 -0.4189 0.11694 0.11353 0.0001 1.0000 0.0245
-9.500 -0.4163 0.11350 0.11011 -0.0030 1.0000 0.0246
-9.250 -0.4126 0.10985 0.10650 -0.0056 1.0000 0.0247
-9.000 -0.4080 0.10609 0.10276 -0.0079 1.0000 0.0247
-8.500 -0.3957 0.09819 0.09493 -0.0103 1.0000 0.0249
-8.250 -0.3850 0.09502 0.09176 -0.0092 1.0000 0.0254
-8.000 -0.3780 0.09195 0.08873 -0.0104 1.0000 0.0259
-7.750 -0.3718 0.08892 0.08573 -0.0120 1.0000 0.0267
-7.500 -0.3656 0.08589 0.08275 -0.0146 1.0000 0.0285
-7.250 -0.3521 0.08109 0.07795 -0.0267 1.0000 0.0305
-7.000 -0.3300 0.07570 0.07247 -0.0352 0.9678 0.0307
-6.750 -0.3057 0.07035 0.06699 -0.0418 0.9336 0.0308
-6.500 -0.2851 0.06554 0.06201 -0.0461 0.8999 0.0308
-6.250 -0.2761 0.06170 0.05813 -0.0456 0.8707 0.0314
-6.000 -0.2648 0.05994 0.05632 -0.0439 0.8458 0.0327
-5.750 -0.2468 0.05728 0.05351 -0.0453 0.8267 0.0349
-5.500 -0.2103 0.05303 0.04874 -0.0517 0.8115 0.0385
-5.250 -0.1866 0.04939 0.04477 -0.0534 0.7974 0.0386
-4.750 -0.1496 0.04230 0.03745 -0.0549 0.7708 0.0401
-4.500 -0.1275 0.04002 0.03502 -0.0554 0.7583 0.0412
-4.250 -0.1028 0.03758 0.03234 -0.0561 0.7460 0.0423
-4.000 -0.0763 0.03492 0.02938 -0.0567 0.7339 0.0425
-3.500 -0.0172 0.02885 0.02237 -0.0572 0.7132 0.0379
-3.250 0.0097 0.02676 0.01999 -0.0574 0.7028 0.0377
-3.000 0.0392 0.02538 0.01813 -0.0571 0.6918 0.0389
-2.750 0.0658 0.02320 0.01570 -0.0573 0.6804 0.0394
-2.500 0.0940 0.02204 0.01422 -0.0571 0.6681 0.0390
-2.250 0.1219 0.02080 0.01271 -0.0570 0.6548 0.0389
-2.000 0.1498 0.01952 0.01118 -0.0570 0.6408 0.0391
-1.750 0.1776 0.01840 0.00986 -0.0569 0.6261 0.0394
-1.500 0.2053 0.01753 0.00882 -0.0569 0.6103 0.0400
-1.250 0.2327 0.01698 0.00817 -0.0568 0.5934 0.0414
-1.000 0.2605 0.01645 0.00749 -0.0567 0.5758 0.0425
-0.750 0.2883 0.01586 0.00671 -0.0565 0.5579 0.0427
-0.500 0.3160 0.01536 0.00605 -0.0563 0.5400 0.0430
-0.250 0.3435 0.01495 0.00550 -0.0561 0.5217 0.0436
0.000 0.3709 0.01462 0.00504 -0.0559 0.5030 0.0443
0.250 0.3983 0.01435 0.00465 -0.0557 0.4840 0.0452
0.500 0.4257 0.01413 0.00434 -0.0556 0.4644 0.0462
0.750 0.4532 0.01407 0.00417 -0.0555 0.4452 0.0480
1.000 0.4804 0.01382 0.00388 -0.0555 0.4279 0.0503
1.250 0.5078 0.01371 0.00371 -0.0555 0.4127 0.0518
1.500 0.5353 0.01367 0.00360 -0.0555 0.4002 0.0536
1.750 0.5629 0.01369 0.00352 -0.0554 0.3903 0.0561
2.000 0.5904 0.01375 0.00348 -0.0554 0.3820 0.0591
2.250 0.6181 0.01377 0.00348 -0.0554 0.3755 0.0662
2.500 0.6456 0.01379 0.00355 -0.0554 0.3698 0.0955
3.000 0.6978 0.01218 0.00379 -0.0548 0.3607 1.0000
3.250 0.7252 0.01239 0.00394 -0.0547 0.3563 1.0000
3.500 0.7524 0.01263 0.00410 -0.0547 0.3525 1.0000
3.750 0.7794 0.01290 0.00430 -0.0546 0.3494 1.0000
4.000 0.8067 0.01314 0.00451 -0.0545 0.3467 1.0000
4.250 0.8340 0.01336 0.00473 -0.0545 0.3440 1.0000
4.500 0.8612 0.01361 0.00499 -0.0545 0.3413 1.0000
4.750 0.8884 0.01387 0.00525 -0.0544 0.3389 1.0000
5.000 0.9153 0.01416 0.00552 -0.0544 0.3366 1.0000
5.250 0.9422 0.01447 0.00583 -0.0543 0.3343 1.0000
5.500 0.9690 0.01475 0.00613 -0.0542 0.3304 1.0000
5.750 0.9957 0.01497 0.00641 -0.0541 0.3244 1.0000
6.000 1.0218 0.01527 0.00668 -0.0540 0.3187 1.0000
6.250 1.0483 0.01556 0.00703 -0.0539 0.3146 1.0000
6.500 1.0748 0.01580 0.00737 -0.0538 0.3103 1.0000
6.750 1.1010 0.01606 0.00768 -0.0537 0.3053 1.0000
7.000 1.1267 0.01639 0.00803 -0.0535 0.3002 1.0000
7.250 1.1528 0.01659 0.00838 -0.0534 0.2940 1.0000
7.500 1.1786 0.01687 0.00875 -0.0532 0.2896 1.0000
7.750 1.2040 0.01722 0.00914 -0.0530 0.2858 1.0000
8.000 1.2299 0.01745 0.00956 -0.0529 0.2804 1.0000
8.250 1.2551 0.01770 0.00992 -0.0526 0.2734 1.0000
8.500 1.2800 0.01791 0.01028 -0.0524 0.2630 1.0000
8.750 1.3044 0.01811 0.01059 -0.0521 0.2459 1.0000
9.000 1.3277 0.01843 0.01091 -0.0517 0.2164 1.0000
9.250 1.3439 0.01948 0.01162 -0.0507 0.1629 1.0000
9.500 1.3583 0.02086 0.01282 -0.0495 0.1281 1.0000
9.750 1.3713 0.02230 0.01411 -0.0482 0.0934 1.0000
10.000 1.3817 0.02387 0.01552 -0.0467 0.0668 1.0000
10.250 1.3933 0.02520 0.01685 -0.0451 0.0572 1.0000
10.500 1.4045 0.02644 0.01817 -0.0436 0.0497 1.0000
10.750 1.4142 0.02770 0.01953 -0.0419 0.0427 1.0000
11.000 1.4182 0.02912 0.02102 -0.0395 0.0362 1.0000
11.250 1.4215 0.03075 0.02271 -0.0376 0.0300 1.0000
11.500 1.4236 0.03267 0.02472 -0.0362 0.0256 1.0000
11.750 1.4234 0.03504 0.02716 -0.0352 0.0229 1.0000
12.000 1.4230 0.03767 0.02991 -0.0348 0.0210 1.0000
12.250 1.4204 0.04073 0.03308 -0.0347 0.0196 1.0000
12.500 1.4147 0.04434 0.03680 -0.0350 0.0186 1.0000
12.750 1.4092 0.04808 0.04068 -0.0355 0.0180 1.0000
13.000 1.4029 0.05206 0.04483 -0.0363 0.0175 1.0000
13.250 1.3952 0.05636 0.04928 -0.0372 0.0170 1.0000
13.500 1.3863 0.06090 0.05397 -0.0383 0.0166 1.0000
13.750 1.3766 0.06566 0.05887 -0.0396 0.0163 1.0000
14.000 1.3663 0.07051 0.06386 -0.0409 0.0159 1.0000
14.250 1.3561 0.07542 0.06889 -0.0422 0.0156 1.0000
14.500 1.3464 0.08041 0.07401 -0.0437 0.0153 1.0000
14.750 1.3370 0.08542 0.07912 -0.0452 0.0150 1.0000
15.000 1.3278 0.09046 0.08426 -0.0468 0.0147 1.0000
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Polar data table (+)
Polar graphs
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