GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 200,000 Max Cl/Cd: 67.02 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe290-il-200000-n5.txt Download as CSV file: xf-goe290-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 290 (MVA 290) 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7326 0.06396 0.05909 -0.0709 1.0000 0.0428
-13.500 -0.7752 0.05417 0.04896 -0.0790 1.0000 0.0429
-13.250 -0.7982 0.04846 0.04299 -0.0831 1.0000 0.0431
-13.000 -0.8152 0.04453 0.03883 -0.0845 1.0000 0.0434
-12.750 -0.8304 0.04170 0.03580 -0.0835 1.0000 0.0437
-12.500 -0.8470 0.03972 0.03364 -0.0801 1.0000 0.0440
-12.250 -0.8601 0.03804 0.03177 -0.0760 1.0000 0.0443
-12.000 -0.8673 0.03641 0.02993 -0.0724 1.0000 0.0447
-11.750 -0.8542 0.03488 0.02828 -0.0718 0.9967 0.0451
-11.500 -0.8260 0.03358 0.02693 -0.0736 0.9914 0.0455
-11.250 -0.7978 0.03234 0.02563 -0.0752 0.9847 0.0461
-11.000 -0.7702 0.03113 0.02433 -0.0765 0.9770 0.0467
-10.750 -0.7418 0.02991 0.02298 -0.0779 0.9688 0.0474
-10.500 -0.7167 0.02877 0.02169 -0.0784 0.9574 0.0483
-10.250 -0.6924 0.02763 0.02037 -0.0787 0.9448 0.0493
-10.000 -0.6691 0.02652 0.01903 -0.0785 0.9300 0.0502
-9.750 -0.6449 0.02569 0.01820 -0.0783 0.9114 0.0509
-9.500 -0.6197 0.02495 0.01741 -0.0782 0.8883 0.0516
-9.250 -0.5940 0.02420 0.01655 -0.0780 0.8623 0.0525
-9.000 -0.5697 0.02350 0.01568 -0.0774 0.8368 0.0535
-8.750 -0.5466 0.02284 0.01483 -0.0766 0.8128 0.0545
-8.500 -0.5235 0.02224 0.01400 -0.0757 0.7908 0.0558
-8.250 -0.5002 0.02169 0.01333 -0.0750 0.7699 0.0569
-8.000 -0.4764 0.02124 0.01281 -0.0744 0.7494 0.0581
-7.750 -0.4521 0.02082 0.01227 -0.0739 0.7287 0.0595
-7.500 -0.4277 0.02038 0.01168 -0.0733 0.7079 0.0611
-7.250 -0.4030 0.01996 0.01106 -0.0727 0.6874 0.0627
-7.000 -0.3788 0.01950 0.01051 -0.0722 0.6681 0.0641
-6.750 -0.3539 0.01913 0.01005 -0.0718 0.6506 0.0657
-6.500 -0.3284 0.01880 0.00961 -0.0714 0.6357 0.0679
-6.250 -0.3025 0.01852 0.00916 -0.0710 0.6234 0.0702
-6.000 -0.2773 0.01811 0.00871 -0.0707 0.6128 0.0724
-5.750 -0.2513 0.01779 0.00832 -0.0704 0.6040 0.0748
-5.500 -0.2249 0.01751 0.00794 -0.0702 0.5955 0.0775
-5.250 -0.1988 0.01720 0.00756 -0.0699 0.5884 0.0803
-5.000 -0.1723 0.01688 0.00721 -0.0698 0.5813 0.0836
-4.750 -0.1454 0.01666 0.00690 -0.0696 0.5750 0.0872
-4.500 -0.1188 0.01639 0.00659 -0.0695 0.5699 0.0911
-4.250 -0.0914 0.01614 0.00633 -0.0694 0.5649 0.0958
-4.000 -0.0640 0.01591 0.00609 -0.0694 0.5601 0.1014
-3.750 -0.0365 0.01571 0.00586 -0.0694 0.5556 0.1090
-3.500 -0.0092 0.01551 0.00566 -0.0693 0.5515 0.1206
-3.250 0.0184 0.01525 0.00546 -0.0693 0.5474 0.1410
-3.000 0.0454 0.01487 0.00524 -0.0694 0.5433 0.1779
-2.750 0.0718 0.01445 0.00520 -0.0694 0.5396 0.2662
-2.500 0.0999 0.01440 0.00518 -0.0694 0.5362 0.3037
-2.250 0.1282 0.01440 0.00517 -0.0694 0.5330 0.3267
-2.000 0.1566 0.01442 0.00516 -0.0695 0.5295 0.3449
-1.750 0.1852 0.01440 0.00516 -0.0696 0.5254 0.3617
-1.500 0.2135 0.01437 0.00517 -0.0696 0.5211 0.3772
-1.250 0.2417 0.01436 0.00516 -0.0696 0.5170 0.3914
-1.000 0.2701 0.01439 0.00514 -0.0697 0.5132 0.4045
-0.750 0.2984 0.01440 0.00515 -0.0697 0.5099 0.4176
-0.500 0.3266 0.01436 0.00518 -0.0698 0.5064 0.4323
-0.250 0.3548 0.01433 0.00521 -0.0698 0.5028 0.4488
0.000 0.3829 0.01430 0.00524 -0.0698 0.4993 0.4663
0.250 0.4108 0.01427 0.00526 -0.0698 0.4958 0.4864
0.500 0.4384 0.01426 0.00529 -0.0697 0.4923 0.5102
0.750 0.4659 0.01419 0.00536 -0.0696 0.4887 0.5397
1.000 0.4931 0.01411 0.00544 -0.0694 0.4850 0.5771
1.250 0.5195 0.01399 0.00554 -0.0691 0.4813 0.6301
1.500 0.5445 0.01384 0.00564 -0.0683 0.4776 0.6998
1.750 0.5687 0.01373 0.00575 -0.0671 0.4742 0.7795
2.000 0.5955 0.01373 0.00589 -0.0664 0.4709 0.8557
2.250 0.6293 0.01376 0.00603 -0.0672 0.4667 0.9151
2.500 0.6674 0.01383 0.00612 -0.0693 0.4615 0.9549
2.750 0.7062 0.01394 0.00618 -0.0715 0.4570 0.9821
3.000 0.7464 0.01409 0.00625 -0.0742 0.4535 1.0000
3.250 0.7710 0.01420 0.00638 -0.0736 0.4497 1.0000
3.500 0.7958 0.01432 0.00651 -0.0731 0.4456 1.0000
3.750 0.8209 0.01445 0.00663 -0.0726 0.4416 1.0000
4.000 0.8461 0.01458 0.00670 -0.0722 0.4374 1.0000
4.250 0.8713 0.01472 0.00683 -0.0717 0.4324 1.0000
4.500 0.8964 0.01484 0.00698 -0.0713 0.4261 1.0000
4.750 0.9214 0.01496 0.00706 -0.0708 0.4200 1.0000
5.000 0.9465 0.01511 0.00722 -0.0703 0.4138 1.0000
5.250 0.9715 0.01526 0.00738 -0.0699 0.4068 1.0000
5.500 0.9959 0.01542 0.00750 -0.0693 0.3997 1.0000
5.750 1.0204 0.01558 0.00769 -0.0688 0.3899 1.0000
6.000 1.0440 0.01577 0.00785 -0.0682 0.3793 1.0000
6.250 1.0667 0.01600 0.00803 -0.0674 0.3670 1.0000
6.500 1.0890 0.01626 0.00826 -0.0665 0.3533 1.0000
6.750 1.1106 0.01657 0.00852 -0.0656 0.3393 1.0000
7.000 1.1306 0.01696 0.00883 -0.0645 0.3235 1.0000
7.250 1.1489 0.01742 0.00921 -0.0631 0.3069 1.0000
7.500 1.1661 0.01794 0.00965 -0.0616 0.2919 1.0000
7.750 1.1832 0.01847 0.01013 -0.0601 0.2800 1.0000
8.000 1.1992 0.01903 0.01065 -0.0584 0.2705 1.0000
8.250 1.2139 0.01962 0.01121 -0.0566 0.2619 1.0000
8.500 1.2261 0.02022 0.01180 -0.0544 0.2550 1.0000
8.750 1.2388 0.02087 0.01244 -0.0523 0.2479 1.0000
9.000 1.2490 0.02168 0.01322 -0.0501 0.2415 1.0000
9.250 1.2632 0.02235 0.01394 -0.0485 0.2361 1.0000
9.500 1.2756 0.02316 0.01476 -0.0469 0.2306 1.0000
9.750 1.2858 0.02412 0.01573 -0.0451 0.2257 1.0000
10.000 1.2979 0.02503 0.01669 -0.0437 0.2215 1.0000
10.250 1.3109 0.02595 0.01766 -0.0425 0.2170 1.0000
10.500 1.3204 0.02713 0.01888 -0.0411 0.2116 1.0000
10.750 1.3271 0.02859 0.02034 -0.0397 0.2069 1.0000
11.000 1.3400 0.02968 0.02153 -0.0389 0.2026 1.0000
11.250 1.3498 0.03106 0.02298 -0.0381 0.1973 1.0000
11.500 1.3554 0.03283 0.02479 -0.0371 0.1921 1.0000
11.750 1.3653 0.03432 0.02636 -0.0365 0.1859 1.0000
12.000 1.3696 0.03636 0.02844 -0.0359 0.1760 1.0000
12.250 1.3690 0.03896 0.03103 -0.0353 0.1491 1.0000
12.500 1.3481 0.04372 0.03559 -0.0348 0.1228 1.0000
12.750 1.3362 0.04769 0.03950 -0.0344 0.1122 1.0000
13.000 1.3298 0.05117 0.04301 -0.0341 0.1057 1.0000
13.250 1.3258 0.05446 0.04635 -0.0340 0.1005 1.0000
13.500 1.3223 0.05774 0.04969 -0.0340 0.0961 1.0000
13.750 1.3221 0.06072 0.05275 -0.0340 0.0906 1.0000
14.000 1.3194 0.06404 0.05614 -0.0342 0.0821 1.0000
14.250 1.3059 0.06871 0.06077 -0.0345 0.0588 1.0000
14.500 1.2879 0.07408 0.06609 -0.0352 0.0484 1.0000
14.750 1.2770 0.07870 0.07074 -0.0358 0.0448 1.0000
15.000 1.2689 0.08303 0.07514 -0.0364 0.0430 1.0000
15.250 1.2621 0.08727 0.07946 -0.0372 0.0416 1.0000
15.500 1.2559 0.09151 0.08378 -0.0380 0.0406 1.0000
15.750 1.2507 0.09567 0.08804 -0.0388 0.0398 1.0000
16.000 1.2454 0.09987 0.09234 -0.0398 0.0391 1.0000
16.250 1.2396 0.10422 0.09678 -0.0408 0.0385 1.0000
16.500 1.2333 0.10869 0.10135 -0.0420 0.0379 1.0000
16.750 1.2271 0.11321 0.10597 -0.0433 0.0374 1.0000
17.000 1.2207 0.11779 0.11064 -0.0447 0.0369 1.0000
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