GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 200,000 Max Cl/Cd: 73.59 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe315-il-200000.txt Download as CSV file: xf-goe315-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3729 0.10275 0.09911 -0.0172 1.0000 0.0334
-8.750 -0.3765 0.10077 0.09718 -0.0208 1.0000 0.0336
-8.500 -0.3813 0.09860 0.09508 -0.0240 1.0000 0.0338
-8.250 -0.3719 0.09335 0.08985 -0.0224 1.0000 0.0343
-8.000 -0.3605 0.08967 0.08618 -0.0207 1.0000 0.0349
-7.750 -0.3568 0.08689 0.08344 -0.0207 1.0000 0.0354
-7.500 -0.3559 0.08427 0.08088 -0.0210 1.0000 0.0359
-7.250 -0.3527 0.08143 0.07808 -0.0220 1.0000 0.0366
-7.000 -0.3481 0.07845 0.07514 -0.0237 1.0000 0.0374
-6.750 -0.3424 0.07538 0.07209 -0.0257 1.0000 0.0384
-6.500 -0.3343 0.07221 0.06893 -0.0287 1.0000 0.0398
-6.250 -0.3163 0.06957 0.06609 -0.0371 1.0000 0.0413
-6.000 -0.3091 0.06574 0.06220 -0.0382 1.0000 0.0417
-5.750 -0.3092 0.06204 0.05866 -0.0355 1.0000 0.0423
-5.500 -0.2991 0.05923 0.05592 -0.0351 0.9972 0.0431
-5.250 -0.2636 0.05528 0.05190 -0.0404 0.9882 0.0451
-5.000 -0.2229 0.05124 0.04770 -0.0469 0.9771 0.0481
-4.750 -0.1710 0.04713 0.04302 -0.0551 0.9636 0.0519
-4.500 -0.1423 0.04289 0.03888 -0.0583 0.9517 0.0536
-4.250 -0.1075 0.04002 0.03593 -0.0617 0.9373 0.0567
-4.000 -0.0563 0.04062 0.03574 -0.0650 0.9199 0.0634
-3.750 -0.0322 0.03426 0.02952 -0.0678 0.9027 0.0656
-3.500 -0.0036 0.03200 0.02717 -0.0691 0.8831 0.0686
-3.250 0.0324 0.03382 0.02824 -0.0685 0.8622 0.0771
-3.000 0.0495 0.02859 0.02313 -0.0690 0.8438 0.0800
-2.750 0.0724 0.02716 0.02159 -0.0685 0.8257 0.0853
-2.500 0.0977 0.02595 0.01998 -0.0678 0.8089 0.0941
-2.250 0.1207 0.02453 0.01847 -0.0672 0.7928 0.0994
-2.000 0.1453 0.02338 0.01704 -0.0665 0.7776 0.1101
-1.750 0.1697 0.02245 0.01587 -0.0659 0.7630 0.1238
-1.500 0.1936 0.02137 0.01464 -0.0653 0.7491 0.1392
-1.250 0.2172 0.02025 0.01344 -0.0648 0.7361 0.1580
-0.250 0.3339 0.01652 0.00831 -0.0600 0.6820 0.0753
0.000 0.3604 0.01550 0.00719 -0.0593 0.6695 0.0715
0.250 0.3872 0.01490 0.00645 -0.0586 0.6594 0.0702
0.500 0.4137 0.01444 0.00595 -0.0580 0.6485 0.0714
0.750 0.4399 0.01396 0.00544 -0.0573 0.6385 0.0706
1.000 0.4659 0.01358 0.00500 -0.0566 0.6293 0.0706
1.250 0.4916 0.01324 0.00470 -0.0559 0.6186 0.0716
1.500 0.5173 0.01300 0.00444 -0.0553 0.6093 0.0735
1.750 0.5432 0.01285 0.00424 -0.0547 0.6001 0.0767
2.000 0.5689 0.01268 0.00408 -0.0541 0.5901 0.0851
2.250 0.5951 0.01260 0.00395 -0.0535 0.5806 0.0983
2.500 0.6482 0.01062 0.00386 -0.0588 0.5684 1.0000
2.750 0.6734 0.01076 0.00393 -0.0581 0.5572 1.0000
3.000 0.6985 0.01094 0.00402 -0.0574 0.5466 1.0000
3.250 0.7234 0.01112 0.00409 -0.0567 0.5342 1.0000
3.500 0.7475 0.01127 0.00415 -0.0558 0.5177 1.0000
3.750 0.7716 0.01140 0.00423 -0.0549 0.4999 1.0000
4.000 0.7957 0.01154 0.00432 -0.0540 0.4823 1.0000
4.250 0.8201 0.01168 0.00444 -0.0532 0.4658 1.0000
4.500 0.8445 0.01184 0.00458 -0.0524 0.4484 1.0000
4.750 0.8685 0.01201 0.00470 -0.0516 0.4294 1.0000
5.000 0.8924 0.01218 0.00485 -0.0508 0.4059 1.0000
5.250 0.9154 0.01244 0.00500 -0.0499 0.3788 1.0000
5.500 0.9381 0.01277 0.00523 -0.0489 0.3540 1.0000
5.750 0.9610 0.01313 0.00552 -0.0481 0.3324 1.0000
6.000 0.9837 0.01353 0.00585 -0.0472 0.3134 1.0000
6.250 1.0065 0.01394 0.00622 -0.0464 0.2970 1.0000
6.500 1.0288 0.01437 0.00660 -0.0455 0.2799 1.0000
6.750 1.0511 0.01481 0.00700 -0.0447 0.2632 1.0000
7.000 1.0734 0.01523 0.00742 -0.0438 0.2436 1.0000
7.250 1.0951 0.01572 0.00789 -0.0429 0.2223 1.0000
7.500 1.1158 0.01630 0.00839 -0.0418 0.1915 1.0000
7.750 1.1250 0.01804 0.00944 -0.0396 0.0898 1.0000
8.000 1.1395 0.01932 0.01062 -0.0378 0.0696 1.0000
8.250 1.1561 0.02029 0.01160 -0.0363 0.0617 1.0000
8.500 1.1735 0.02112 0.01254 -0.0348 0.0580 1.0000
8.750 1.1896 0.02200 0.01351 -0.0332 0.0553 1.0000
9.000 1.2025 0.02306 0.01462 -0.0312 0.0529 1.0000
9.250 1.2113 0.02437 0.01596 -0.0289 0.0509 1.0000
9.500 1.2227 0.02542 0.01712 -0.0268 0.0494 1.0000
9.750 1.2309 0.02657 0.01837 -0.0242 0.0483 1.0000
10.000 1.2374 0.02780 0.01967 -0.0215 0.0473 1.0000
10.250 1.2438 0.02913 0.02105 -0.0191 0.0460 1.0000
10.500 1.2503 0.03058 0.02252 -0.0170 0.0448 1.0000
10.750 1.2576 0.03232 0.02427 -0.0151 0.0435 1.0000
11.000 1.2723 0.03452 0.02648 -0.0138 0.0422 1.0000
11.250 1.2861 0.03603 0.02812 -0.0124 0.0416 1.0000
11.500 1.2993 0.03765 0.02990 -0.0112 0.0408 1.0000
11.750 1.3121 0.03945 0.03185 -0.0100 0.0398 1.0000
12.000 1.3230 0.04131 0.03384 -0.0088 0.0385 1.0000
12.250 1.3364 0.04341 0.03609 -0.0078 0.0377 1.0000
12.500 1.3476 0.04575 0.03860 -0.0067 0.0371 1.0000
12.750 1.3565 0.04831 0.04131 -0.0057 0.0365 1.0000
13.000 1.3658 0.05123 0.04436 -0.0049 0.0357 1.0000
13.250 1.3751 0.05606 0.04940 -0.0046 0.0348 1.0000
13.500 1.3683 0.06070 0.05432 -0.0036 0.0345 1.0000
13.750 1.3586 0.06437 0.05823 -0.0027 0.0345 1.0000
14.000 1.3460 0.06822 0.06232 -0.0023 0.0345 1.0000
14.250 1.3329 0.07200 0.06630 -0.0024 0.0345 1.0000
14.500 1.3186 0.07594 0.07046 -0.0030 0.0346 1.0000
14.750 1.3034 0.08008 0.07479 -0.0042 0.0348 1.0000
15.000 1.2855 0.08479 0.07971 -0.0061 0.0349 1.0000
15.250 1.2653 0.09018 0.08532 -0.0089 0.0352 1.0000
15.500 1.2358 0.09725 0.09269 -0.0134 0.0359 1.0000
15.750 1.1738 0.11130 0.10717 -0.0237 0.0372 1.0000
16.000 1.1183 0.12775 0.12391 -0.0353 0.0386 1.0000
16.250 1.0710 0.14492 0.14121 -0.0463 0.0410 1.0000
16.500 1.0576 0.15366 0.14995 -0.0503 0.0422 1.0000
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Polar data table (+)
Polar graphs
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