GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Reynolds number: 500,000 Max Cl/Cd: 101.64 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe319-il-500000.txt Download as CSV file: xf-goe319-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 319 (HANSA-BRANDENBURG II) 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 -0.1978 0.08764 0.08532 -0.0375 0.9102 0.0262
-7.750 -0.1925 0.08498 0.08259 -0.0385 0.8894 0.0267
-7.500 -0.1872 0.08185 0.07939 -0.0421 0.8688 0.0275
-7.250 -0.1745 0.07705 0.07448 -0.0540 0.8487 0.0278
-7.000 -0.1602 0.07288 0.07022 -0.0583 0.8338 0.0279
-6.750 -0.1490 0.07025 0.06754 -0.0575 0.8203 0.0280
-6.500 -0.1351 0.06781 0.06506 -0.0576 0.8077 0.0282
-6.250 -0.1191 0.06527 0.06245 -0.0590 0.7963 0.0285
-6.000 -0.1011 0.06256 0.05966 -0.0614 0.7851 0.0289
-5.750 -0.0809 0.05964 0.05667 -0.0645 0.7748 0.0294
-5.500 -0.0591 0.05662 0.05354 -0.0678 0.7655 0.0301
-5.250 -0.0164 0.05086 0.04747 -0.0783 0.7568 0.0320
-5.000 0.0034 0.04722 0.04371 -0.0801 0.7491 0.0323
-4.750 0.0227 0.04505 0.04152 -0.0805 0.7409 0.0325
-4.500 0.0438 0.04312 0.03949 -0.0812 0.7322 0.0328
-4.250 0.0670 0.04112 0.03743 -0.0821 0.7231 0.0332
-4.000 0.0916 0.03911 0.03528 -0.0831 0.7143 0.0341
-3.750 0.1310 0.03433 0.03002 -0.0863 0.7071 0.0370
-3.500 0.1518 0.03239 0.02806 -0.0865 0.6986 0.0373
-3.250 0.1751 0.03097 0.02658 -0.0867 0.6901 0.0378
-3.000 0.1997 0.02959 0.02511 -0.0869 0.6809 0.0385
-2.750 0.2259 0.02804 0.02343 -0.0872 0.6720 0.0398
-2.500 0.2563 0.02482 0.01977 -0.0873 0.6629 0.0431
-2.250 0.2812 0.02376 0.01866 -0.0873 0.6523 0.0437
-2.000 0.3068 0.02278 0.01757 -0.0872 0.6425 0.0447
-1.750 0.3360 0.02090 0.01530 -0.0868 0.6340 0.0495
-1.500 0.3615 0.01997 0.01434 -0.0868 0.6256 0.0504
-1.250 0.3883 0.01917 0.01348 -0.0867 0.6170 0.0521
-1.000 0.4163 0.01802 0.01198 -0.0862 0.6088 0.0574
-0.750 0.4429 0.01722 0.01118 -0.0861 0.5998 0.0589
-0.500 0.4724 0.01811 0.01176 -0.0854 0.5906 0.0647
-0.250 0.4975 0.01582 0.00947 -0.0855 0.5818 0.0677
0.000 0.5279 0.01284 0.00571 -0.0838 0.5745 0.0429
0.250 0.5556 0.01231 0.00511 -0.0835 0.5662 0.0429
0.500 0.5830 0.01204 0.00473 -0.0831 0.5577 0.0426
0.750 0.6106 0.01166 0.00432 -0.0828 0.5494 0.0423
1.000 0.6375 0.01134 0.00394 -0.0824 0.5409 0.0424
1.250 0.6644 0.01092 0.00352 -0.0821 0.5325 0.0429
1.500 0.6910 0.01072 0.00329 -0.0817 0.5237 0.0438
1.750 0.7182 0.01058 0.00317 -0.0814 0.5147 0.0450
2.000 0.7449 0.01054 0.00310 -0.0810 0.5049 0.0466
2.250 0.7723 0.01050 0.00305 -0.0808 0.4938 0.0487
2.500 0.7991 0.01043 0.00297 -0.0805 0.4824 0.0516
2.750 0.8259 0.01047 0.00297 -0.0801 0.4699 0.0556
3.000 0.8526 0.01047 0.00299 -0.0798 0.4552 0.0710
3.250 0.8906 0.00879 0.00324 -0.0825 0.4358 1.0000
3.500 0.9158 0.00901 0.00332 -0.0819 0.4124 1.0000
3.750 0.9398 0.00933 0.00346 -0.0812 0.3828 1.0000
4.000 0.9629 0.00975 0.00366 -0.0803 0.3509 1.0000
4.500 1.0093 0.01060 0.00417 -0.0788 0.3054 1.0000
5.000 1.0578 0.01127 0.00465 -0.0776 0.2806 1.0000
5.250 1.0819 0.01161 0.00491 -0.0770 0.2726 1.0000
5.500 1.1068 0.01187 0.00514 -0.0765 0.2662 1.0000
5.750 1.1307 0.01221 0.00542 -0.0759 0.2604 1.0000
6.000 1.1553 0.01250 0.00569 -0.0753 0.2559 1.0000
6.250 1.1801 0.01275 0.00595 -0.0749 0.2517 1.0000
6.500 1.2041 0.01306 0.00623 -0.0743 0.2475 1.0000
6.750 1.2271 0.01345 0.00658 -0.0736 0.2433 1.0000
7.000 1.2512 0.01374 0.00689 -0.0730 0.2401 1.0000
7.250 1.2757 0.01399 0.00716 -0.0725 0.2368 1.0000
7.500 1.2994 0.01429 0.00747 -0.0720 0.2332 1.0000
7.750 1.3219 0.01468 0.00783 -0.0712 0.2294 1.0000
8.000 1.3433 0.01515 0.00828 -0.0703 0.2257 1.0000
8.250 1.3673 0.01539 0.00858 -0.0698 0.2232 1.0000
8.500 1.3906 0.01568 0.00891 -0.0692 0.2202 1.0000
8.750 1.4129 0.01602 0.00927 -0.0685 0.2170 1.0000
9.000 1.4337 0.01645 0.00969 -0.0676 0.2136 1.0000
9.250 1.4531 0.01700 0.01023 -0.0665 0.2099 1.0000
9.500 1.4757 0.01723 0.01055 -0.0658 0.2069 1.0000
9.750 1.4972 0.01752 0.01089 -0.0650 0.2028 1.0000
10.000 1.5154 0.01795 0.01131 -0.0638 0.1985 1.0000
10.250 1.5311 0.01853 0.01189 -0.0621 0.1944 1.0000
10.500 1.5511 0.01882 0.01227 -0.0611 0.1911 1.0000
10.750 1.5695 0.01921 0.01272 -0.0600 0.1871 1.0000
11.000 1.5851 0.01978 0.01328 -0.0586 0.1830 1.0000
11.250 1.6008 0.02037 0.01392 -0.0572 0.1786 1.0000
11.500 1.6192 0.02080 0.01443 -0.0563 0.1738 1.0000
11.750 1.6340 0.02148 0.01511 -0.0551 0.1691 1.0000
12.000 1.6477 0.02226 0.01592 -0.0538 0.1649 1.0000
12.250 1.6641 0.02290 0.01663 -0.0528 0.1602 1.0000
12.500 1.6769 0.02380 0.01754 -0.0516 0.1554 1.0000
12.750 1.6890 0.02478 0.01856 -0.0505 0.1513 1.0000
13.000 1.7026 0.02569 0.01954 -0.0495 0.1470 1.0000
13.250 1.7127 0.02690 0.02077 -0.0484 0.1428 1.0000
13.500 1.7218 0.02823 0.02214 -0.0473 0.1388 1.0000
13.750 1.7332 0.02942 0.02340 -0.0465 0.1344 1.0000
14.000 1.7398 0.03104 0.02504 -0.0455 0.1300 1.0000
14.250 1.7464 0.03271 0.02677 -0.0447 0.1264 1.0000
14.500 1.7554 0.03420 0.02835 -0.0440 0.1229 1.0000
14.750 1.7604 0.03610 0.03029 -0.0432 0.1194 1.0000
15.000 1.7610 0.03843 0.03265 -0.0424 0.1159 1.0000
15.250 1.7685 0.04014 0.03447 -0.0419 0.1127 1.0000
15.500 1.7718 0.04229 0.03668 -0.0413 0.1088 1.0000
15.750 1.7696 0.04503 0.03945 -0.0408 0.1052 1.0000
16.000 1.7724 0.04734 0.04185 -0.0404 0.1018 1.0000
16.250 1.7742 0.04981 0.04440 -0.0402 0.0979 1.0000
16.500 1.7699 0.05302 0.04766 -0.0401 0.0943 1.0000
16.750 1.7692 0.05589 0.05062 -0.0400 0.0910 1.0000
17.000 1.7681 0.05889 0.05371 -0.0401 0.0870 1.0000
17.250 1.7602 0.06278 0.05764 -0.0404 0.0832 1.0000
17.500 1.7566 0.06620 0.06116 -0.0407 0.0792 1.0000
17.750 1.7475 0.07043 0.06544 -0.0413 0.0750 1.0000
18.000 1.7369 0.07492 0.07000 -0.0421 0.0712 1.0000
18.250 1.7241 0.07979 0.07495 -0.0430 0.0673 1.0000
18.500 1.7071 0.08537 0.08060 -0.0443 0.0640 1.0000
18.750 1.6923 0.09074 0.08606 -0.0457 0.0605 1.0000
19.000 1.6718 0.09703 0.09244 -0.0475 0.0577 1.0000
19.250 1.6530 0.10324 0.09874 -0.0494 0.0549 1.0000
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Polar data table (+)
Polar graphs
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