GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 500,000 Max Cl/Cd: 95.15 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe315-il-500000.txt Download as CSV file: xf-goe315-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3593 0.08690 0.08467 -0.0185 1.0000 0.0215
-7.750 -0.3588 0.08414 0.08194 -0.0194 1.0000 0.0220
-7.500 -0.3624 0.08141 0.07926 -0.0208 1.0000 0.0225
-7.250 -0.3590 0.07734 0.07519 -0.0279 1.0000 0.0228
-7.000 -0.3506 0.07305 0.07087 -0.0329 1.0000 0.0229
-6.750 -0.3432 0.06855 0.06633 -0.0356 1.0000 0.0231
-6.500 -0.3405 0.06554 0.06338 -0.0336 1.0000 0.0233
-5.750 -0.2545 0.05436 0.05206 -0.0473 0.9668 0.0251
-5.500 -0.1968 0.04854 0.04587 -0.0584 0.9431 0.0277
-4.750 -0.1158 0.03783 0.03448 -0.0663 0.8333 0.0290
-4.500 -0.0957 0.03594 0.03239 -0.0661 0.8111 0.0298
-4.250 -0.0740 0.03392 0.03016 -0.0659 0.7940 0.0308
-4.000 -0.0422 0.03251 0.02826 -0.0650 0.7801 0.0337
-3.750 -0.0241 0.02841 0.02389 -0.0648 0.7679 0.0344
-3.500 -0.0028 0.02671 0.02210 -0.0645 0.7554 0.0350
-3.250 0.0201 0.02536 0.02064 -0.0642 0.7433 0.0358
-3.000 0.0440 0.02405 0.01918 -0.0638 0.7320 0.0370
-2.750 0.0696 0.02282 0.01772 -0.0631 0.7208 0.0394
-2.500 0.0960 0.02111 0.01551 -0.0619 0.7092 0.0423
-2.250 0.1196 0.01965 0.01403 -0.0617 0.6960 0.0434
-2.000 0.1443 0.01876 0.01304 -0.0613 0.6815 0.0450
-1.750 0.1700 0.01796 0.01208 -0.0607 0.6664 0.0476
-1.500 0.1966 0.01704 0.01077 -0.0598 0.6514 0.0528
-1.250 0.2215 0.01598 0.00969 -0.0594 0.6352 0.0547
-1.000 0.2473 0.01539 0.00898 -0.0590 0.6186 0.0578
-0.750 0.2738 0.01489 0.00821 -0.0583 0.6040 0.0655
-0.500 0.2996 0.01412 0.00743 -0.0581 0.5915 0.0687
-0.250 0.3278 0.01540 0.00854 -0.0575 0.5803 0.0771
0.000 0.3550 0.01221 0.00505 -0.0564 0.5717 0.0536
0.250 0.3819 0.01120 0.00391 -0.0556 0.5632 0.0442
0.500 0.4083 0.01081 0.00344 -0.0550 0.5547 0.0432
0.750 0.4346 0.01050 0.00310 -0.0545 0.5465 0.0432
1.000 0.4605 0.01026 0.00282 -0.0540 0.5383 0.0436
1.250 0.4869 0.01007 0.00264 -0.0536 0.5300 0.0452
1.750 0.5394 0.00980 0.00232 -0.0527 0.5118 0.0468
2.000 0.5658 0.00973 0.00222 -0.0523 0.5018 0.0482
2.250 0.5922 0.00970 0.00215 -0.0518 0.4909 0.0500
2.500 0.6189 0.00965 0.00208 -0.0515 0.4792 0.0527
2.750 0.6455 0.00963 0.00206 -0.0511 0.4674 0.0616
3.000 0.6997 0.00769 0.00221 -0.0575 0.4511 1.0000
3.250 0.7250 0.00780 0.00225 -0.0569 0.4361 1.0000
3.500 0.7500 0.00795 0.00230 -0.0562 0.4162 1.0000
3.750 0.7745 0.00814 0.00238 -0.0555 0.3912 1.0000
4.000 0.7985 0.00840 0.00250 -0.0547 0.3625 1.0000
4.250 0.8220 0.00872 0.00266 -0.0539 0.3315 1.0000
4.500 0.8451 0.00910 0.00288 -0.0531 0.2998 1.0000
4.750 0.8683 0.00948 0.00311 -0.0523 0.2737 1.0000
5.000 0.8920 0.00981 0.00334 -0.0516 0.2536 1.0000
5.250 0.9157 0.01016 0.00359 -0.0509 0.2353 1.0000
5.500 0.9394 0.01050 0.00384 -0.0502 0.2168 1.0000
5.750 0.9633 0.01083 0.00410 -0.0495 0.1984 1.0000
6.000 0.9863 0.01124 0.00438 -0.0487 0.1735 1.0000
6.250 1.0023 0.01240 0.00506 -0.0471 0.0888 1.0000
6.500 1.0216 0.01323 0.00570 -0.0458 0.0502 1.0000
6.750 1.0437 0.01374 0.00614 -0.0449 0.0428 1.0000
7.000 1.0665 0.01416 0.00661 -0.0441 0.0405 1.0000
7.250 1.0888 0.01463 0.00713 -0.0432 0.0389 1.0000
7.500 1.1104 0.01516 0.00771 -0.0422 0.0375 1.0000
7.750 1.1310 0.01577 0.00837 -0.0411 0.0362 1.0000
8.000 1.1497 0.01654 0.00922 -0.0397 0.0347 1.0000
8.250 1.1692 0.01719 0.00995 -0.0385 0.0340 1.0000
8.500 1.1883 0.01784 0.01067 -0.0373 0.0334 1.0000
8.750 1.2061 0.01857 0.01147 -0.0358 0.0327 1.0000
9.000 1.2227 0.01935 0.01231 -0.0343 0.0317 1.0000
9.250 1.2379 0.02020 0.01323 -0.0326 0.0308 1.0000
9.500 1.2508 0.02115 0.01425 -0.0306 0.0299 1.0000
9.750 1.2608 0.02226 0.01541 -0.0283 0.0291 1.0000
10.000 1.2649 0.02360 0.01680 -0.0252 0.0284 1.0000
10.250 1.2618 0.02563 0.01888 -0.0212 0.0276 1.0000
10.500 1.2741 0.02627 0.01961 -0.0193 0.0270 1.0000
10.750 1.2842 0.02721 0.02065 -0.0174 0.0265 1.0000
11.000 1.2932 0.02832 0.02184 -0.0156 0.0258 1.0000
11.250 1.3015 0.02959 0.02319 -0.0139 0.0252 1.0000
11.500 1.3096 0.03096 0.02463 -0.0124 0.0246 1.0000
11.750 1.3173 0.03242 0.02613 -0.0112 0.0239 1.0000
12.000 1.3244 0.03401 0.02776 -0.0100 0.0231 1.0000
12.250 1.3337 0.03582 0.02958 -0.0089 0.0225 1.0000
12.500 1.3452 0.03811 0.03193 -0.0077 0.0216 1.0000
12.750 1.3482 0.03976 0.03374 -0.0068 0.0212 1.0000
13.000 1.3528 0.04163 0.03574 -0.0061 0.0207 1.0000
13.250 1.3567 0.04364 0.03789 -0.0056 0.0202 1.0000
13.500 1.3608 0.04581 0.04018 -0.0051 0.0197 1.0000
13.750 1.3644 0.04801 0.04248 -0.0048 0.0192 1.0000
14.000 1.3681 0.05022 0.04477 -0.0047 0.0188 1.0000
14.250 1.3702 0.05262 0.04725 -0.0048 0.0184 1.0000
14.500 1.3712 0.05516 0.04985 -0.0051 0.0180 1.0000
14.750 1.3742 0.05778 0.05254 -0.0050 0.0177 1.0000
15.000 1.3739 0.06141 0.05628 -0.0046 0.0171 1.0000
15.250 1.3651 0.06520 0.06026 -0.0059 0.0169 1.0000
15.500 1.3576 0.06923 0.06446 -0.0071 0.0168 1.0000
15.750 1.3481 0.07368 0.06910 -0.0088 0.0165 1.0000
16.000 1.3375 0.07858 0.07420 -0.0108 0.0163 1.0000
16.250 1.3273 0.08366 0.07946 -0.0129 0.0161 1.0000
16.500 1.3151 0.08926 0.08523 -0.0155 0.0159 1.0000
16.750 1.3019 0.09527 0.09142 -0.0185 0.0157 1.0000
17.000 1.2874 0.10178 0.09810 -0.0220 0.0156 1.0000
17.250 1.2704 0.10904 0.10555 -0.0260 0.0155 1.0000
17.500 1.2543 0.11643 0.11311 -0.0304 0.0155 1.0000
17.750 1.2346 0.12498 0.12183 -0.0356 0.0154 1.0000
18.000 1.2123 0.13454 0.13158 -0.0416 0.0155 1.0000
18.250 1.1860 0.14554 0.14275 -0.0487 0.0157 1.0000
18.500 1.1551 0.15854 0.15594 -0.0572 0.0159 1.0000
18.750 1.1186 0.17418 0.17174 -0.0672 0.0164 1.0000
19.000 1.0585 0.20133 0.19901 -0.0823 0.0175 1.0000
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