GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.93 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe323-il-1000000.txt Download as CSV file: xf-goe323-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3831 0.11678 0.11391 0.0097 0.6238 0.0189
-9.750 -0.3764 0.11366 0.11078 0.0083 0.6206 0.0195
-8.750 -0.3680 0.09649 0.09360 -0.0030 0.6087 0.0209
-8.500 -0.3584 0.09388 0.09096 -0.0033 0.6049 0.0211
-7.750 -0.2375 0.07563 0.07280 -0.0135 0.5868 0.0225
-7.500 -0.2341 0.07213 0.06931 -0.0150 0.5845 0.0231
-7.000 -0.3023 0.07611 0.07318 -0.0174 0.5866 0.0228
-6.750 -0.2801 0.06777 0.06475 -0.0320 0.5847 0.0243
-6.500 -0.2602 0.06250 0.05940 -0.0377 0.5821 0.0244
-6.250 -0.2470 0.05723 0.05407 -0.0411 0.5795 0.0246
-6.000 -0.2284 0.05498 0.05176 -0.0423 0.5764 0.0248
-5.750 -0.2081 0.05277 0.04949 -0.0437 0.5729 0.0250
-5.500 -0.1862 0.05028 0.04695 -0.0454 0.5704 0.0253
-5.250 -0.1629 0.04759 0.04420 -0.0473 0.5679 0.0257
-5.000 -0.1385 0.04471 0.04122 -0.0493 0.5654 0.0264
-4.750 -0.1025 0.03803 0.03417 -0.0532 0.5632 0.0284
-4.500 -0.0822 0.03281 0.02872 -0.0547 0.5610 0.0288
-4.250 -0.0582 0.03148 0.02732 -0.0551 0.5581 0.0291
-4.000 -0.0333 0.03020 0.02596 -0.0554 0.5548 0.0294
-3.750 -0.0075 0.02866 0.02434 -0.0557 0.5518 0.0298
-3.500 0.0189 0.02695 0.02252 -0.0560 0.5485 0.0305
-3.250 0.0503 0.02406 0.01910 -0.0555 0.5455 0.0330
-3.000 0.0737 0.02034 0.01511 -0.0558 0.5424 0.0337
-2.750 0.1004 0.01940 0.01410 -0.0558 0.5384 0.0340
-2.500 0.1278 0.01851 0.01315 -0.0558 0.5356 0.0344
-2.250 0.1554 0.01769 0.01225 -0.0558 0.5326 0.0350
-2.000 0.1839 0.01464 0.00864 -0.0550 0.5301 0.0325
-1.750 0.2116 0.01332 0.00714 -0.0548 0.5272 0.0320
-1.500 0.2397 0.01242 0.00607 -0.0546 0.5240 0.0319
-1.250 0.2680 0.01169 0.00523 -0.0544 0.5213 0.0319
-1.000 0.2965 0.01112 0.00460 -0.0543 0.5187 0.0321
-0.750 0.3251 0.01080 0.00422 -0.0542 0.5157 0.0327
-0.500 0.3536 0.01051 0.00388 -0.0541 0.5125 0.0332
-0.250 0.3813 0.00989 0.00323 -0.0539 0.5092 0.0338
0.000 0.4094 0.00967 0.00300 -0.0538 0.5056 0.0345
0.250 0.4380 0.00946 0.00282 -0.0538 0.5026 0.0351
0.500 0.4666 0.00927 0.00264 -0.0537 0.4988 0.0358
0.750 0.4950 0.00912 0.00248 -0.0537 0.4943 0.0366
1.000 0.5234 0.00902 0.00235 -0.0536 0.4896 0.0375
1.250 0.5522 0.00892 0.00227 -0.0536 0.4859 0.0383
1.500 0.5806 0.00870 0.00207 -0.0536 0.4814 0.0403
1.750 0.6091 0.00865 0.00200 -0.0536 0.4764 0.0419
2.000 0.6378 0.00860 0.00196 -0.0536 0.4717 0.0437
2.250 0.6665 0.00850 0.00187 -0.0536 0.4665 0.0460
2.500 0.6950 0.00847 0.00183 -0.0537 0.4608 0.0495
2.750 0.7236 0.00843 0.00181 -0.0537 0.4551 0.0548
3.000 0.7522 0.00839 0.00179 -0.0537 0.4477 0.0668
3.250 0.7837 0.00645 0.00200 -0.0551 0.4395 1.0000
3.500 0.8114 0.00657 0.00203 -0.0550 0.4274 1.0000
3.750 0.8390 0.00671 0.00209 -0.0549 0.4117 1.0000
4.000 0.8664 0.00688 0.00217 -0.0548 0.3932 1.0000
4.250 0.8935 0.00711 0.00229 -0.0547 0.3739 1.0000
4.500 0.9204 0.00736 0.00244 -0.0545 0.3555 1.0000
4.750 0.9472 0.00763 0.00261 -0.0544 0.3391 1.0000
5.000 0.9741 0.00788 0.00279 -0.0543 0.3253 1.0000
5.250 1.0011 0.00812 0.00296 -0.0542 0.3138 1.0000
5.750 1.0552 0.00856 0.00332 -0.0541 0.2953 1.0000
6.000 1.0820 0.00881 0.00352 -0.0540 0.2860 1.0000
6.250 1.1090 0.00903 0.00370 -0.0540 0.2771 1.0000
6.500 1.1358 0.00926 0.00391 -0.0539 0.2691 1.0000
6.750 1.1627 0.00949 0.00410 -0.0539 0.2614 1.0000
7.000 1.1893 0.00973 0.00432 -0.0538 0.2543 1.0000
7.250 1.2160 0.00996 0.00453 -0.0538 0.2473 1.0000
7.500 1.2423 0.01024 0.00478 -0.0537 0.2400 1.0000
7.750 1.2687 0.01048 0.00501 -0.0537 0.2324 1.0000
8.000 1.2945 0.01079 0.00528 -0.0536 0.2240 1.0000
8.250 1.3204 0.01107 0.00554 -0.0535 0.2163 1.0000
8.500 1.3460 0.01138 0.00583 -0.0534 0.2092 1.0000
8.750 1.3716 0.01168 0.00611 -0.0532 0.2020 1.0000
9.000 1.3967 0.01203 0.00644 -0.0531 0.1946 1.0000
9.250 1.4218 0.01234 0.00674 -0.0529 0.1881 1.0000
9.500 1.4463 0.01272 0.00710 -0.0527 0.1814 1.0000
9.750 1.4711 0.01304 0.00743 -0.0526 0.1753 1.0000
10.000 1.4946 0.01349 0.00784 -0.0523 0.1679 1.0000
10.250 1.5189 0.01384 0.00820 -0.0521 0.1616 1.0000
10.500 1.5414 0.01434 0.00867 -0.0517 0.1534 1.0000
10.750 1.5640 0.01480 0.00911 -0.0513 0.1452 1.0000
11.000 1.5853 0.01535 0.00963 -0.0509 0.1351 1.0000
11.250 1.6034 0.01615 0.01034 -0.0501 0.1192 1.0000
11.500 1.6167 0.01730 0.01134 -0.0489 0.0988 1.0000
11.750 1.6294 0.01840 0.01237 -0.0477 0.0871 1.0000
12.000 1.6417 0.01940 0.01336 -0.0464 0.0794 1.0000
12.250 1.6474 0.02069 0.01464 -0.0445 0.0723 1.0000
12.500 1.6520 0.02237 0.01631 -0.0435 0.0634 1.0000
12.750 1.6399 0.02623 0.02002 -0.0434 0.0393 1.0000
13.000 1.6234 0.03092 0.02467 -0.0437 0.0225 1.0000
13.250 1.6215 0.03388 0.02768 -0.0436 0.0193 1.0000
13.500 1.6199 0.03675 0.03060 -0.0435 0.0177 1.0000
13.750 1.6204 0.03938 0.03330 -0.0433 0.0168 1.0000
14.000 1.6199 0.04209 0.03609 -0.0432 0.0161 1.0000
14.250 1.6174 0.04502 0.03910 -0.0430 0.0156 1.0000
14.500 1.6126 0.04822 0.04237 -0.0429 0.0150 1.0000
14.750 1.6061 0.05166 0.04589 -0.0428 0.0145 1.0000
15.000 1.6010 0.05499 0.04931 -0.0428 0.0142 1.0000
15.250 1.5990 0.05814 0.05254 -0.0430 0.0139 1.0000
15.500 1.5956 0.06157 0.05606 -0.0434 0.0137 1.0000
15.750 1.5909 0.06520 0.05978 -0.0438 0.0134 1.0000
16.000 1.5857 0.06899 0.06366 -0.0443 0.0131 1.0000
16.250 1.5795 0.07296 0.06771 -0.0450 0.0129 1.0000
16.500 1.5717 0.07719 0.07203 -0.0457 0.0127 1.0000
16.750 1.5624 0.08176 0.07670 -0.0466 0.0125 1.0000
17.000 1.5513 0.08666 0.08170 -0.0477 0.0123 1.0000
17.250 1.5382 0.09191 0.08705 -0.0490 0.0121 1.0000
17.500 1.5236 0.09753 0.09278 -0.0505 0.0120 1.0000
17.750 1.5072 0.10356 0.09892 -0.0523 0.0118 1.0000
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