GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Reynolds number: 500,000 Max Cl/Cd: 105.27 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe321-il-500000.txt Download as CSV file: xf-goe321-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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 -0.2977 0.08873 0.08580 -0.0203 0.7530 0.0278
-7.750 -0.2910 0.08562 0.08265 -0.0225 0.7456 0.0284
-7.500 -0.2855 0.08235 0.07936 -0.0252 0.7388 0.0291
-7.250 -0.2714 0.07408 0.07098 -0.0442 0.7328 0.0306
-7.000 -0.2613 0.06951 0.06634 -0.0464 0.7267 0.0308
-6.750 -0.2482 0.06682 0.06364 -0.0467 0.7202 0.0310
-6.500 -0.2329 0.06426 0.06103 -0.0475 0.7134 0.0313
-6.250 -0.2159 0.06156 0.05826 -0.0492 0.7072 0.0317
-6.000 -0.1969 0.05860 0.05526 -0.0516 0.7002 0.0322
-5.750 -0.1763 0.05549 0.05203 -0.0542 0.6938 0.0330
-5.500 -0.1407 0.04755 0.04364 -0.0627 0.6884 0.0359
-5.250 -0.1230 0.04491 0.04099 -0.0632 0.6810 0.0363
-5.000 -0.1023 0.04292 0.03892 -0.0637 0.6742 0.0366
-4.750 -0.0797 0.04093 0.03687 -0.0644 0.6663 0.0371
-4.250 -0.0201 0.03574 0.03102 -0.0666 0.6520 0.0417
-4.000 0.0013 0.03168 0.02679 -0.0675 0.6453 0.0424
-3.750 0.0255 0.03015 0.02523 -0.0679 0.6383 0.0429
-3.500 0.0508 0.02884 0.02386 -0.0682 0.6312 0.0437
-3.250 0.0773 0.02742 0.02227 -0.0685 0.6253 0.0450
-3.000 0.1085 0.02490 0.01917 -0.0684 0.6193 0.0495
-2.750 0.1344 0.02329 0.01754 -0.0688 0.6130 0.0503
-2.500 0.1613 0.02221 0.01639 -0.0690 0.6061 0.0512
-2.250 0.1890 0.02122 0.01528 -0.0691 0.5985 0.0529
-2.000 0.2205 0.02200 0.01567 -0.0685 0.5918 0.0573
-1.750 0.2465 0.01887 0.01245 -0.0691 0.5859 0.0594
-1.500 0.2743 0.01811 0.01161 -0.0693 0.5800 0.0613
-1.250 0.3066 0.01399 0.00663 -0.0681 0.5750 0.0426
-1.000 0.3353 0.01332 0.00585 -0.0681 0.5683 0.0425
-0.750 0.3635 0.01276 0.00519 -0.0680 0.5624 0.0428
-0.500 0.3921 0.01236 0.00481 -0.0681 0.5574 0.0438
-0.250 0.4207 0.01208 0.00452 -0.0681 0.5529 0.0451
0.000 0.4491 0.01177 0.00416 -0.0681 0.5485 0.0459
0.250 0.4776 0.01151 0.00386 -0.0681 0.5438 0.0469
0.500 0.5063 0.01128 0.00363 -0.0681 0.5385 0.0480
0.750 0.5348 0.01107 0.00339 -0.0681 0.5340 0.0493
1.000 0.5630 0.01089 0.00319 -0.0682 0.5296 0.0518
1.250 0.5919 0.01078 0.00313 -0.0683 0.5247 0.0554
1.500 0.6206 0.01063 0.00299 -0.0684 0.5189 0.0597
1.750 0.6490 0.01061 0.00293 -0.0684 0.5136 0.0668
2.000 0.6779 0.01044 0.00287 -0.0686 0.5083 0.0891
2.250 0.7041 0.00830 0.00296 -0.0686 0.5027 1.0000
2.500 0.7321 0.00844 0.00297 -0.0685 0.4968 1.0000
2.750 0.7606 0.00849 0.00300 -0.0686 0.4909 1.0000
3.000 0.7888 0.00857 0.00303 -0.0686 0.4843 1.0000
3.250 0.8170 0.00868 0.00308 -0.0686 0.4779 1.0000
3.500 0.8453 0.00874 0.00314 -0.0687 0.4701 1.0000
3.750 0.8733 0.00885 0.00319 -0.0687 0.4621 1.0000
4.000 0.9015 0.00893 0.00325 -0.0688 0.4520 1.0000
4.250 0.9295 0.00903 0.00333 -0.0688 0.4403 1.0000
4.500 0.9572 0.00916 0.00341 -0.0689 0.4250 1.0000
4.750 0.9843 0.00935 0.00350 -0.0688 0.4030 1.0000
5.000 1.0105 0.00967 0.00367 -0.0687 0.3735 1.0000
5.250 1.0357 0.01010 0.00393 -0.0685 0.3448 1.0000
5.500 1.0607 0.01056 0.00425 -0.0682 0.3215 1.0000
5.750 1.0859 0.01099 0.00458 -0.0680 0.3009 1.0000
6.000 1.1107 0.01145 0.00492 -0.0678 0.2805 1.0000
6.250 1.1353 0.01192 0.00528 -0.0675 0.2602 1.0000
6.500 1.1597 0.01237 0.00564 -0.0672 0.2415 1.0000
6.750 1.1840 0.01283 0.00602 -0.0669 0.2275 1.0000
7.000 1.2079 0.01330 0.00641 -0.0665 0.2175 1.0000
7.250 1.2326 0.01366 0.00677 -0.0662 0.2110 1.0000
7.500 1.2564 0.01409 0.00717 -0.0658 0.2056 1.0000
7.750 1.2795 0.01456 0.00762 -0.0653 0.2013 1.0000
8.000 1.3040 0.01489 0.00799 -0.0650 0.1988 1.0000
8.250 1.3277 0.01527 0.00841 -0.0646 0.1963 1.0000
8.500 1.3506 0.01569 0.00884 -0.0640 0.1933 1.0000
8.750 1.3721 0.01620 0.00933 -0.0634 0.1899 1.0000
9.000 1.3927 0.01676 0.00990 -0.0626 0.1867 1.0000
9.250 1.4159 0.01709 0.01031 -0.0621 0.1846 1.0000
9.500 1.4379 0.01748 0.01076 -0.0615 0.1824 1.0000
9.750 1.4589 0.01793 0.01125 -0.0608 0.1803 1.0000
10.000 1.4784 0.01845 0.01180 -0.0599 0.1778 1.0000
10.250 1.4955 0.01910 0.01245 -0.0586 0.1749 1.0000
10.500 1.5105 0.01981 0.01319 -0.0571 0.1723 1.0000
10.750 1.5286 0.02019 0.01367 -0.0559 0.1704 1.0000
11.000 1.5458 0.02066 0.01422 -0.0548 0.1675 1.0000
11.250 1.5611 0.02127 0.01488 -0.0535 0.1642 1.0000
11.500 1.5723 0.02219 0.01581 -0.0519 0.1604 1.0000
11.750 1.5860 0.02302 0.01670 -0.0508 0.1568 1.0000
12.000 1.6048 0.02353 0.01732 -0.0503 0.1524 1.0000
12.250 1.6180 0.02450 0.01831 -0.0495 0.1477 1.0000
12.500 1.6291 0.02570 0.01956 -0.0486 0.1434 1.0000
12.750 1.6480 0.02635 0.02030 -0.0484 0.1365 1.0000
13.000 1.6612 0.02752 0.02149 -0.0480 0.1256 1.0000
13.250 1.6572 0.03036 0.02405 -0.0472 0.0883 1.0000
13.500 1.6361 0.03493 0.02844 -0.0459 0.0618 1.0000
13.750 1.6159 0.03952 0.03293 -0.0448 0.0425 1.0000
14.000 1.6018 0.04363 0.03702 -0.0441 0.0324 1.0000
14.250 1.5931 0.04727 0.04071 -0.0436 0.0280 1.0000
14.500 1.5852 0.05093 0.04444 -0.0434 0.0257 1.0000
14.750 1.5793 0.05446 0.04806 -0.0433 0.0243 1.0000
15.000 1.5739 0.05805 0.05176 -0.0434 0.0232 1.0000
15.250 1.5668 0.06200 0.05581 -0.0437 0.0224 1.0000
15.500 1.5570 0.06642 0.06033 -0.0442 0.0216 1.0000
15.750 1.5449 0.07126 0.06529 -0.0450 0.0210 1.0000
16.000 1.5350 0.07591 0.07006 -0.0458 0.0206 1.0000
16.250 1.5261 0.08049 0.07476 -0.0467 0.0202 1.0000
16.500 1.5157 0.08538 0.07978 -0.0477 0.0198 1.0000
16.750 1.5039 0.09058 0.08509 -0.0490 0.0194 1.0000
17.000 1.4912 0.09605 0.09069 -0.0505 0.0191 1.0000
17.250 1.4769 0.10185 0.09661 -0.0522 0.0188 1.0000
17.500 1.4618 0.10794 0.10282 -0.0541 0.0186 1.0000
17.750 1.4466 0.11417 0.10916 -0.0563 0.0184 1.0000
18.000 1.4309 0.12054 0.11565 -0.0586 0.0182 1.0000
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