GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 500,000 Max Cl/Cd: 96.53 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe290-il-500000.txt Download as CSV file: xf-goe290-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9048 0.06138 0.05767 -0.0729 1.0000 0.0385
-15.250 -0.9247 0.05500 0.05111 -0.0778 1.0000 0.0386
-15.000 -0.9357 0.05020 0.04617 -0.0814 1.0000 0.0388
-14.750 -0.9421 0.04630 0.04214 -0.0842 1.0000 0.0390
-14.500 -0.9453 0.04314 0.03888 -0.0860 1.0000 0.0392
-14.250 -0.9468 0.04054 0.03616 -0.0870 1.0000 0.0394
-14.000 -0.9472 0.03842 0.03394 -0.0872 1.0000 0.0397
-13.750 -0.9472 0.03665 0.03209 -0.0864 1.0000 0.0400
-13.500 -0.9490 0.03519 0.03053 -0.0844 1.0000 0.0403
-13.250 -0.9568 0.03404 0.02929 -0.0805 1.0000 0.0406
-13.000 -0.9612 0.03289 0.02804 -0.0767 1.0000 0.0408
-12.750 -0.9632 0.03176 0.02678 -0.0731 1.0000 0.0411
-12.500 -0.9628 0.03066 0.02557 -0.0696 1.0000 0.0415
-12.250 -0.9600 0.02961 0.02439 -0.0663 1.0000 0.0418
-12.000 -0.9325 0.02821 0.02280 -0.0678 0.9971 0.0423
-11.750 -0.9013 0.02690 0.02130 -0.0698 0.9942 0.0427
-11.500 -0.8708 0.02520 0.01958 -0.0716 0.9913 0.0434
-11.250 -0.8375 0.02435 0.01874 -0.0734 0.9875 0.0440
-11.000 -0.8013 0.02359 0.01795 -0.0757 0.9842 0.0448
-10.750 -0.7644 0.02273 0.01702 -0.0782 0.9812 0.0456
-10.500 -0.7352 0.02190 0.01611 -0.0789 0.9734 0.0463
-10.250 -0.7048 0.02109 0.01520 -0.0798 0.9662 0.0470
-10.000 -0.6794 0.02044 0.01444 -0.0795 0.9553 0.0476
-9.750 -0.6577 0.01954 0.01347 -0.0786 0.9416 0.0483
-9.500 -0.6362 0.01880 0.01272 -0.0775 0.9248 0.0491
-9.250 -0.6139 0.01830 0.01219 -0.0764 0.9016 0.0498
-9.000 -0.5916 0.01789 0.01167 -0.0752 0.8700 0.0507
-8.750 -0.5688 0.01755 0.01115 -0.0740 0.8379 0.0517
-8.500 -0.5449 0.01724 0.01065 -0.0732 0.8118 0.0527
-8.250 -0.5199 0.01696 0.01018 -0.0726 0.7885 0.0536
-8.000 -0.4966 0.01629 0.00944 -0.0719 0.7659 0.0548
-7.750 -0.4715 0.01597 0.00904 -0.0714 0.7416 0.0559
-7.500 -0.4458 0.01572 0.00867 -0.0710 0.7148 0.0572
-7.250 -0.4199 0.01550 0.00829 -0.0706 0.6854 0.0587
-7.000 -0.3935 0.01536 0.00796 -0.0702 0.6590 0.0600
-6.750 -0.3688 0.01489 0.00741 -0.0698 0.6376 0.0619
-6.500 -0.3421 0.01471 0.00715 -0.0696 0.6210 0.0637
-6.250 -0.3150 0.01454 0.00688 -0.0695 0.6079 0.0658
-6.000 -0.2873 0.01437 0.00661 -0.0693 0.5979 0.0676
-5.750 -0.2615 0.01394 0.00616 -0.0691 0.5892 0.0701
-5.500 -0.2338 0.01375 0.00592 -0.0691 0.5821 0.0727
-5.250 -0.2055 0.01363 0.00573 -0.0691 0.5753 0.0752
-5.000 -0.1790 0.01326 0.00533 -0.0689 0.5691 0.0785
-4.750 -0.1511 0.01307 0.00511 -0.0689 0.5638 0.0818
-4.500 -0.1225 0.01293 0.00492 -0.0690 0.5589 0.0846
-4.250 -0.0952 0.01260 0.00460 -0.0689 0.5544 0.0890
-4.000 -0.0670 0.01248 0.00441 -0.0689 0.5500 0.0932
-3.750 -0.0389 0.01229 0.00422 -0.0690 0.5461 0.0985
-3.500 -0.0102 0.01210 0.00405 -0.0691 0.5424 0.1050
-3.250 0.0181 0.01188 0.00388 -0.0692 0.5379 0.1164
-3.000 0.0459 0.01160 0.00370 -0.0692 0.5332 0.1457
-2.750 0.0715 0.01101 0.00354 -0.0692 0.5284 0.2597
-2.500 0.1002 0.01084 0.00354 -0.0693 0.5253 0.3080
-2.250 0.1293 0.01080 0.00354 -0.0695 0.5221 0.3308
-2.000 0.1585 0.01078 0.00354 -0.0697 0.5190 0.3468
-1.750 0.1876 0.01078 0.00354 -0.0698 0.5158 0.3605
-1.500 0.2167 0.01085 0.00355 -0.0700 0.5121 0.3726
-1.250 0.2455 0.01087 0.00358 -0.0701 0.5084 0.3840
-1.000 0.2749 0.01084 0.00358 -0.0703 0.5057 0.3954
-0.750 0.3040 0.01081 0.00359 -0.0705 0.5028 0.4070
-0.500 0.3331 0.01079 0.00359 -0.0707 0.4998 0.4180
-0.250 0.3621 0.01079 0.00359 -0.0709 0.4967 0.4305
0.000 0.3908 0.01080 0.00361 -0.0710 0.4931 0.4439
0.250 0.4196 0.01082 0.00366 -0.0711 0.4895 0.4594
0.500 0.4484 0.01073 0.00367 -0.0713 0.4866 0.4802
0.750 0.4770 0.01064 0.00370 -0.0714 0.4837 0.5105
1.000 0.5050 0.01050 0.00374 -0.0715 0.4806 0.5574
1.250 0.5319 0.01027 0.00379 -0.0713 0.4774 0.6390
1.500 0.5567 0.01002 0.00389 -0.0705 0.4742 0.7521
1.750 0.5795 0.00986 0.00405 -0.0690 0.4709 0.8536
2.000 0.6047 0.00977 0.00413 -0.0679 0.4675 0.9217
2.250 0.6396 0.00979 0.00418 -0.0691 0.4633 0.9604
2.500 0.6786 0.00986 0.00421 -0.0713 0.4592 0.9813
2.750 0.7203 0.01001 0.00428 -0.0743 0.4550 0.9930
3.000 0.7648 0.01010 0.00436 -0.0778 0.4515 0.9995
3.250 0.7911 0.01014 0.00441 -0.0776 0.4480 1.0000
3.500 0.8160 0.01019 0.00445 -0.0770 0.4443 1.0000
3.750 0.8409 0.01026 0.00448 -0.0764 0.4404 1.0000
4.000 0.8657 0.01040 0.00455 -0.0758 0.4360 1.0000
4.250 0.8915 0.01041 0.00461 -0.0754 0.4309 1.0000
4.500 0.9172 0.01046 0.00464 -0.0750 0.4243 1.0000
4.750 0.9426 0.01056 0.00469 -0.0746 0.4175 1.0000
5.000 0.9691 0.01062 0.00476 -0.0743 0.4101 1.0000
5.250 0.9947 0.01075 0.00484 -0.0739 0.4029 1.0000
5.500 1.0214 0.01085 0.00496 -0.0738 0.3955 1.0000
5.750 1.0468 0.01100 0.00507 -0.0734 0.3866 1.0000
6.000 1.0728 0.01115 0.00520 -0.0731 0.3754 1.0000
6.250 1.0975 0.01137 0.00536 -0.0726 0.3605 1.0000
6.500 1.1211 0.01165 0.00556 -0.0720 0.3427 1.0000
6.750 1.1432 0.01205 0.00584 -0.0712 0.3221 1.0000
7.000 1.1646 0.01250 0.00617 -0.0703 0.3007 1.0000
7.250 1.1851 0.01300 0.00656 -0.0692 0.2820 1.0000
7.500 1.2056 0.01348 0.00697 -0.0682 0.2682 1.0000
7.750 1.2258 0.01396 0.00739 -0.0671 0.2577 1.0000
8.000 1.2465 0.01439 0.00778 -0.0662 0.2488 1.0000
8.250 1.2662 0.01485 0.00821 -0.0650 0.2413 1.0000
8.500 1.2863 0.01527 0.00861 -0.0639 0.2344 1.0000
8.750 1.3034 0.01579 0.00910 -0.0624 0.2275 1.0000
9.000 1.3224 0.01615 0.00948 -0.0611 0.2223 1.0000
9.250 1.3374 0.01666 0.00998 -0.0592 0.2166 1.0000
9.500 1.3527 0.01719 0.01051 -0.0575 0.2112 1.0000
9.750 1.3694 0.01769 0.01102 -0.0560 0.2043 1.0000
10.000 1.3821 0.01841 0.01173 -0.0541 0.1975 1.0000
10.250 1.3989 0.01896 0.01229 -0.0529 0.1890 1.0000
10.500 1.4119 0.01974 0.01305 -0.0512 0.1785 1.0000
10.750 1.4105 0.02142 0.01450 -0.0483 0.1370 1.0000
11.000 1.3971 0.02411 0.01701 -0.0447 0.1097 1.0000
11.250 1.3960 0.02625 0.01914 -0.0429 0.0995 1.0000
11.500 1.3966 0.02845 0.02135 -0.0416 0.0910 1.0000
11.750 1.3987 0.03065 0.02356 -0.0406 0.0791 1.0000
12.500 1.3711 0.04133 0.03418 -0.0382 0.0405 1.0000
12.750 1.3711 0.04418 0.03710 -0.0380 0.0393 1.0000
13.000 1.3700 0.04718 0.04017 -0.0378 0.0384 1.0000
13.250 1.3676 0.05034 0.04341 -0.0376 0.0376 1.0000
13.500 1.3643 0.05366 0.04681 -0.0376 0.0370 1.0000
13.750 1.3614 0.05697 0.05020 -0.0376 0.0364 1.0000
14.000 1.3598 0.06016 0.05348 -0.0376 0.0361 1.0000
14.250 1.3570 0.06355 0.05695 -0.0378 0.0357 1.0000
14.500 1.3536 0.06707 0.06055 -0.0380 0.0353 1.0000
14.750 1.3495 0.07067 0.06424 -0.0382 0.0349 1.0000
15.000 1.3445 0.07445 0.06811 -0.0386 0.0345 1.0000
15.250 1.3388 0.07842 0.07216 -0.0391 0.0342 1.0000
15.500 1.3332 0.08239 0.07621 -0.0396 0.0338 1.0000
15.750 1.3262 0.08659 0.08049 -0.0402 0.0335 1.0000
16.000 1.3188 0.09093 0.08491 -0.0409 0.0333 1.0000
16.250 1.3116 0.09529 0.08934 -0.0417 0.0330 1.0000
16.500 1.3033 0.09983 0.09397 -0.0426 0.0328 1.0000
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Polar data table (+)
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