GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 200,000 Max Cl/Cd: 74.82 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe323-il-200000-n5.txt Download as CSV file: xf-goe323-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3087 0.09442 0.08979 -0.0075 0.6445 0.0372
-7.750 -0.3076 0.09060 0.08601 -0.0143 0.6413 0.0387
-7.500 -0.3015 0.08603 0.08142 -0.0235 0.6381 0.0389
-7.250 -0.2890 0.08160 0.07694 -0.0288 0.6349 0.0390
-7.000 -0.2781 0.07866 0.07400 -0.0274 0.6316 0.0393
-6.750 -0.2653 0.07586 0.07115 -0.0276 0.6287 0.0396
-6.500 -0.2507 0.07286 0.06815 -0.0293 0.6251 0.0401
-6.250 -0.2345 0.06969 0.06495 -0.0320 0.6214 0.0408
-6.000 -0.2166 0.06636 0.06155 -0.0354 0.6181 0.0416
-5.750 -0.1855 0.06106 0.05595 -0.0454 0.6154 0.0449
-5.500 -0.1596 0.05650 0.05106 -0.0503 0.6131 0.0452
-5.250 -0.1433 0.05334 0.04793 -0.0505 0.6104 0.0455
-5.000 -0.1242 0.05083 0.04542 -0.0511 0.6072 0.0459
-4.750 -0.1030 0.04841 0.04294 -0.0520 0.6040 0.0465
-4.500 -0.0797 0.04594 0.04036 -0.0532 0.6009 0.0472
-4.250 -0.0550 0.04337 0.03763 -0.0545 0.5981 0.0480
-3.750 0.0046 0.03326 0.02641 -0.0577 0.5935 0.0389
-3.500 0.0295 0.03147 0.02456 -0.0580 0.5904 0.0385
-3.250 0.0556 0.02949 0.02240 -0.0583 0.5875 0.0382
-3.000 0.0824 0.02749 0.02014 -0.0584 0.5846 0.0380
-2.750 0.1096 0.02561 0.01796 -0.0584 0.5818 0.0379
-2.500 0.1377 0.02377 0.01564 -0.0582 0.5793 0.0386
-2.250 0.1655 0.02244 0.01398 -0.0580 0.5769 0.0391
-2.000 0.1934 0.02129 0.01265 -0.0580 0.5735 0.0392
-1.750 0.2212 0.02029 0.01148 -0.0579 0.5692 0.0393
-1.500 0.2489 0.01942 0.01046 -0.0577 0.5645 0.0396
-1.250 0.2766 0.01872 0.00960 -0.0574 0.5603 0.0400
-1.000 0.3048 0.01809 0.00892 -0.0574 0.5552 0.0405
-0.750 0.3328 0.01753 0.00829 -0.0572 0.5511 0.0411
-0.500 0.3609 0.01709 0.00777 -0.0570 0.5475 0.0423
-0.250 0.3889 0.01671 0.00726 -0.0568 0.5443 0.0439
0.000 0.4170 0.01633 0.00682 -0.0566 0.5403 0.0447
0.250 0.4449 0.01593 0.00642 -0.0565 0.5360 0.0454
0.500 0.4724 0.01551 0.00604 -0.0563 0.5318 0.0463
0.750 0.5000 0.01522 0.00574 -0.0561 0.5282 0.0475
1.000 0.5277 0.01498 0.00554 -0.0559 0.5239 0.0490
1.250 0.5555 0.01482 0.00540 -0.0558 0.5188 0.0516
1.500 0.5831 0.01458 0.00519 -0.0557 0.5141 0.0542
1.750 0.6107 0.01443 0.00500 -0.0555 0.5098 0.0568
2.000 0.6386 0.01432 0.00494 -0.0554 0.5038 0.0600
2.250 0.6663 0.01419 0.00482 -0.0553 0.4979 0.0654
2.500 0.6940 0.01409 0.00472 -0.0551 0.4924 0.0769
2.750 0.7159 0.01272 0.00486 -0.0545 0.4855 0.6377
3.750 0.8364 0.01237 0.00493 -0.0555 0.4531 1.0000
4.000 0.8634 0.01249 0.00497 -0.0552 0.4445 1.0000
4.250 0.8905 0.01262 0.00508 -0.0551 0.4339 1.0000
4.500 0.9173 0.01277 0.00519 -0.0549 0.4224 1.0000
4.750 0.9438 0.01293 0.00529 -0.0546 0.4094 1.0000
5.000 0.9701 0.01314 0.00542 -0.0544 0.3952 1.0000
5.250 0.9959 0.01338 0.00559 -0.0541 0.3809 1.0000
5.500 1.0214 0.01367 0.00579 -0.0538 0.3676 1.0000
5.750 1.0467 0.01399 0.00605 -0.0536 0.3548 1.0000
6.000 1.0718 0.01435 0.00635 -0.0533 0.3429 1.0000
6.250 1.0965 0.01474 0.00668 -0.0529 0.3316 1.0000
6.500 1.1205 0.01518 0.00704 -0.0526 0.3205 1.0000
6.750 1.1449 0.01559 0.00744 -0.0523 0.3095 1.0000
7.000 1.1689 0.01604 0.00785 -0.0519 0.2995 1.0000
7.250 1.1924 0.01652 0.00828 -0.0515 0.2903 1.0000
7.500 1.2164 0.01693 0.00873 -0.0512 0.2825 1.0000
7.750 1.2398 0.01740 0.00919 -0.0508 0.2754 1.0000
8.000 1.2631 0.01786 0.00967 -0.0504 0.2692 1.0000
8.250 1.2863 0.01832 0.01016 -0.0500 0.2627 1.0000
8.500 1.3079 0.01889 0.01072 -0.0495 0.2566 1.0000
8.750 1.3308 0.01934 0.01124 -0.0491 0.2501 1.0000
9.000 1.3518 0.01991 0.01183 -0.0485 0.2436 1.0000
9.250 1.3728 0.02047 0.01244 -0.0480 0.2376 1.0000
9.500 1.3934 0.02105 0.01307 -0.0474 0.2315 1.0000
10.000 1.4313 0.02235 0.01446 -0.0459 0.2199 1.0000
10.250 1.4479 0.02310 0.01526 -0.0451 0.2136 1.0000
10.500 1.4636 0.02390 0.01610 -0.0442 0.2072 1.0000
10.750 1.4762 0.02477 0.01703 -0.0429 0.2003 1.0000
11.000 1.4860 0.02589 0.01817 -0.0417 0.1945 1.0000
11.250 1.4975 0.02701 0.01941 -0.0410 0.1883 1.0000
11.500 1.5053 0.02856 0.02098 -0.0404 0.1827 1.0000
11.750 1.5154 0.03004 0.02255 -0.0401 0.1768 1.0000
12.000 1.5229 0.03185 0.02442 -0.0400 0.1704 1.0000
12.250 1.5294 0.03379 0.02642 -0.0399 0.1646 1.0000
12.500 1.5367 0.03568 0.02840 -0.0398 0.1584 1.0000
12.750 1.5391 0.03803 0.03078 -0.0397 0.1529 1.0000
13.000 1.5458 0.03995 0.03281 -0.0395 0.1470 1.0000
13.250 1.5468 0.04246 0.03537 -0.0394 0.1405 1.0000
13.500 1.5489 0.04487 0.03785 -0.0393 0.1332 1.0000
13.750 1.5464 0.04779 0.04080 -0.0392 0.1262 1.0000
14.000 1.5466 0.05044 0.04353 -0.0392 0.1189 1.0000
14.250 1.5424 0.05358 0.04670 -0.0392 0.1124 1.0000
14.500 1.5384 0.05676 0.04994 -0.0393 0.1059 1.0000
14.750 1.5319 0.06029 0.05352 -0.0395 0.1002 1.0000
15.000 1.5244 0.06416 0.05742 -0.0400 0.0943 1.0000
15.250 1.5162 0.06825 0.06155 -0.0406 0.0893 1.0000
15.500 1.5091 0.07227 0.06564 -0.0413 0.0848 1.0000
15.750 1.4984 0.07691 0.07034 -0.0422 0.0809 1.0000
16.000 1.4922 0.08101 0.07455 -0.0431 0.0761 1.0000
16.250 1.4802 0.08602 0.07964 -0.0443 0.0709 1.0000
16.500 1.4721 0.09058 0.08431 -0.0455 0.0643 1.0000
16.750 1.4592 0.09598 0.08978 -0.0471 0.0543 1.0000
17.000 1.4353 0.10321 0.09700 -0.0495 0.0421 1.0000
17.250 1.4112 0.11072 0.10450 -0.0522 0.0345 1.0000
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