GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il) Reynolds number: 500,000 Max Cl/Cd: 83.95 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe290-il-500000-n5.txt Download as CSV file: xf-goe290-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9115 0.09877 0.09520 -0.0436 1.0000 0.0306
-17.750 -0.9465 0.08890 0.08513 -0.0497 1.0000 0.0307
-17.500 -0.9707 0.08128 0.07734 -0.0544 1.0000 0.0309
-17.250 -0.9910 0.07462 0.07053 -0.0585 1.0000 0.0310
-17.000 -1.0079 0.06880 0.06457 -0.0620 1.0000 0.0311
-16.750 -1.0215 0.06347 0.05910 -0.0653 1.0000 0.0312
-16.500 -1.0324 0.05855 0.05405 -0.0683 1.0000 0.0313
-16.250 -1.0395 0.05426 0.04968 -0.0709 1.0000 0.0315
-16.000 -1.0445 0.05016 0.04552 -0.0735 1.0000 0.0316
-15.750 -1.0470 0.04630 0.04157 -0.0760 1.0000 0.0318
-15.500 -1.0474 0.04273 0.03791 -0.0786 1.0000 0.0320
-15.250 -1.0458 0.03946 0.03455 -0.0809 1.0000 0.0322
-15.000 -1.0427 0.03657 0.03158 -0.0828 1.0000 0.0324
-14.750 -1.0387 0.03407 0.02898 -0.0841 1.0000 0.0326
-14.500 -1.0341 0.03197 0.02679 -0.0848 1.0000 0.0328
-14.250 -1.0293 0.03023 0.02497 -0.0846 1.0000 0.0330
-14.000 -1.0247 0.02880 0.02346 -0.0836 1.0000 0.0332
-13.750 -1.0221 0.02765 0.02225 -0.0815 1.0000 0.0334
-13.500 -1.0209 0.02674 0.02126 -0.0786 0.9985 0.0337
-13.250 -0.9993 0.02568 0.02013 -0.0792 0.9928 0.0340
-13.000 -0.9777 0.02473 0.01909 -0.0794 0.9862 0.0343
-12.750 -0.9533 0.02384 0.01810 -0.0800 0.9800 0.0347
-12.500 -0.9302 0.02306 0.01723 -0.0801 0.9719 0.0351
-12.250 -0.9076 0.02232 0.01640 -0.0799 0.9634 0.0355
-12.000 -0.8866 0.02152 0.01557 -0.0794 0.9541 0.0359
-11.750 -0.8666 0.02087 0.01489 -0.0786 0.9425 0.0363
-11.500 -0.8459 0.02028 0.01425 -0.0777 0.9284 0.0367
-11.000 -0.8053 0.01925 0.01302 -0.0752 0.8686 0.0375
-10.750 -0.7850 0.01885 0.01241 -0.0738 0.8331 0.0380
-10.500 -0.7628 0.01846 0.01185 -0.0730 0.8082 0.0385
-10.250 -0.7395 0.01807 0.01132 -0.0723 0.7880 0.0390
-10.000 -0.7155 0.01769 0.01081 -0.0718 0.7690 0.0395
-9.750 -0.6912 0.01730 0.01030 -0.0713 0.7504 0.0400
-9.500 -0.6669 0.01689 0.00982 -0.0708 0.7308 0.0407
-9.250 -0.6420 0.01658 0.00940 -0.0704 0.7084 0.0414
-9.000 -0.6166 0.01631 0.00901 -0.0700 0.6837 0.0422
-8.750 -0.5910 0.01606 0.00863 -0.0697 0.6586 0.0431
-8.500 -0.5652 0.01581 0.00824 -0.0694 0.6353 0.0440
-8.250 -0.5391 0.01558 0.00787 -0.0691 0.6154 0.0448
-8.000 -0.5131 0.01529 0.00751 -0.0688 0.5992 0.0457
-7.750 -0.4865 0.01506 0.00720 -0.0687 0.5863 0.0468
-7.500 -0.4594 0.01484 0.00691 -0.0685 0.5757 0.0480
-7.250 -0.4322 0.01463 0.00663 -0.0684 0.5672 0.0493
-7.000 -0.4047 0.01441 0.00634 -0.0684 0.5595 0.0506
-6.750 -0.3774 0.01420 0.00610 -0.0683 0.5524 0.0521
-6.500 -0.3495 0.01403 0.00589 -0.0683 0.5465 0.0539
-6.250 -0.3215 0.01386 0.00566 -0.0683 0.5405 0.0557
-6.000 -0.2937 0.01367 0.00544 -0.0682 0.5351 0.0574
-5.750 -0.2658 0.01352 0.00525 -0.0682 0.5305 0.0593
-5.500 -0.2373 0.01336 0.00506 -0.0683 0.5269 0.0614
-5.250 -0.2089 0.01321 0.00488 -0.0683 0.5230 0.0633
-5.000 -0.1807 0.01303 0.00469 -0.0684 0.5192 0.0655
-4.750 -0.1523 0.01291 0.00454 -0.0684 0.5153 0.0680
-4.250 -0.0953 0.01265 0.00422 -0.0686 0.5085 0.0729
-4.000 -0.0666 0.01250 0.00408 -0.0687 0.5052 0.0756
-3.750 -0.0378 0.01240 0.00394 -0.0688 0.5013 0.0783
-3.500 -0.0093 0.01227 0.00379 -0.0689 0.4975 0.0816
-3.250 0.0192 0.01216 0.00367 -0.0690 0.4941 0.0856
-3.000 0.0478 0.01207 0.00355 -0.0691 0.4911 0.0904
-2.750 0.0766 0.01191 0.00344 -0.0692 0.4887 0.0979
-2.500 0.1052 0.01171 0.00333 -0.0694 0.4856 0.1157
-2.250 0.1335 0.01147 0.00321 -0.0695 0.4818 0.1492
-2.000 0.1612 0.01115 0.00307 -0.0696 0.4781 0.1986
-1.750 0.1889 0.01090 0.00304 -0.0697 0.4749 0.2694
-1.500 0.2175 0.01085 0.00304 -0.0698 0.4721 0.2966
-1.250 0.2467 0.01079 0.00304 -0.0700 0.4699 0.3155
-1.000 0.2760 0.01076 0.00304 -0.0702 0.4672 0.3278
-0.750 0.3052 0.01074 0.00304 -0.0704 0.4643 0.3412
-0.500 0.3342 0.01072 0.00305 -0.0706 0.4611 0.3520
-0.250 0.3632 0.01074 0.00305 -0.0707 0.4578 0.3612
0.000 0.3920 0.01075 0.00306 -0.0709 0.4548 0.3717
0.500 0.4501 0.01073 0.00312 -0.0712 0.4498 0.3949
0.750 0.4792 0.01072 0.00314 -0.0714 0.4466 0.4061
1.000 0.5081 0.01071 0.00317 -0.0716 0.4428 0.4197
1.250 0.5367 0.01070 0.00320 -0.0717 0.4391 0.4348
1.500 0.5650 0.01070 0.00324 -0.0718 0.4358 0.4553
1.750 0.5937 0.01065 0.00328 -0.0720 0.4317 0.4812
2.000 0.6221 0.01059 0.00333 -0.0721 0.4260 0.5099
2.250 0.6499 0.01055 0.00338 -0.0721 0.4201 0.5494
2.500 0.6775 0.01045 0.00345 -0.0721 0.4149 0.6061
2.750 0.7045 0.01031 0.00354 -0.0719 0.4090 0.6757
3.000 0.7303 0.01019 0.00364 -0.0715 0.4027 0.7514
3.250 0.7550 0.01010 0.00376 -0.0706 0.3975 0.8232
3.500 0.7791 0.01006 0.00389 -0.0695 0.3906 0.8864
3.750 0.8065 0.01015 0.00400 -0.0692 0.3819 0.9348
4.000 0.8401 0.01030 0.00411 -0.0704 0.3696 0.9658
4.250 0.8749 0.01051 0.00424 -0.0721 0.3542 0.9866
4.500 0.9075 0.01081 0.00442 -0.0733 0.3328 1.0000
4.750 0.9296 0.01121 0.00466 -0.0725 0.3068 1.0000
5.000 0.9512 0.01167 0.00496 -0.0715 0.2801 1.0000
5.250 0.9733 0.01211 0.00527 -0.0707 0.2610 1.0000
5.500 0.9965 0.01247 0.00556 -0.0700 0.2490 1.0000
5.750 1.0196 0.01283 0.00585 -0.0693 0.2395 1.0000
6.000 1.0430 0.01317 0.00614 -0.0687 0.2310 1.0000
6.250 1.0656 0.01354 0.00646 -0.0680 0.2232 1.0000
6.500 1.0895 0.01383 0.00673 -0.0675 0.2180 1.0000
6.750 1.1125 0.01416 0.00703 -0.0668 0.2126 1.0000
7.000 1.1344 0.01454 0.00738 -0.0660 0.2072 1.0000
7.250 1.1578 0.01482 0.00767 -0.0654 0.2032 1.0000
7.500 1.1802 0.01513 0.00798 -0.0646 0.1986 1.0000
7.750 1.2007 0.01554 0.00836 -0.0636 0.1931 1.0000
8.000 1.2218 0.01589 0.00871 -0.0627 0.1881 1.0000
8.250 1.2417 0.01628 0.00909 -0.0616 0.1809 1.0000
8.500 1.2581 0.01673 0.00951 -0.0599 0.1725 1.0000
8.750 1.2576 0.01798 0.01049 -0.0559 0.1268 1.0000
9.000 1.2589 0.01929 0.01169 -0.0525 0.1069 1.0000
9.250 1.2689 0.02024 0.01263 -0.0504 0.0997 1.0000
9.500 1.2809 0.02112 0.01352 -0.0487 0.0939 1.0000
9.750 1.2899 0.02225 0.01464 -0.0470 0.0863 1.0000
10.000 1.2941 0.02379 0.01612 -0.0450 0.0667 1.0000
10.250 1.2836 0.02663 0.01884 -0.0425 0.0382 1.0000
10.500 1.2893 0.02843 0.02067 -0.0414 0.0347 1.0000
10.750 1.2967 0.03020 0.02249 -0.0407 0.0331 1.0000
11.000 1.3039 0.03204 0.02439 -0.0401 0.0320 1.0000
11.250 1.3116 0.03390 0.02631 -0.0396 0.0314 1.0000
11.500 1.3184 0.03591 0.02838 -0.0392 0.0308 1.0000
11.750 1.3240 0.03809 0.03064 -0.0389 0.0303 1.0000
12.000 1.3282 0.04044 0.03306 -0.0386 0.0298 1.0000
12.250 1.3314 0.04295 0.03564 -0.0384 0.0294 1.0000
12.500 1.3334 0.04562 0.03837 -0.0383 0.0290 1.0000
12.750 1.3340 0.04845 0.04129 -0.0382 0.0287 1.0000
13.000 1.3331 0.05148 0.04439 -0.0381 0.0283 1.0000
13.250 1.3338 0.05437 0.04735 -0.0381 0.0280 1.0000
13.500 1.3344 0.05729 0.05035 -0.0381 0.0277 1.0000
13.750 1.3345 0.06029 0.05342 -0.0382 0.0275 1.0000
14.000 1.3337 0.06345 0.05666 -0.0383 0.0273 1.0000
14.250 1.3323 0.06672 0.06001 -0.0385 0.0271 1.0000
14.500 1.3310 0.06998 0.06334 -0.0387 0.0269 1.0000
14.750 1.3284 0.07348 0.06692 -0.0391 0.0267 1.0000
15.000 1.3262 0.07695 0.07046 -0.0394 0.0265 1.0000
15.250 1.3232 0.08059 0.07419 -0.0399 0.0263 1.0000
15.500 1.3198 0.08430 0.07797 -0.0404 0.0261 1.0000
15.750 1.3165 0.08803 0.08178 -0.0409 0.0259 1.0000
16.000 1.3121 0.09200 0.08583 -0.0416 0.0258 1.0000
16.250 1.3084 0.09588 0.08979 -0.0424 0.0256 1.0000
16.500 1.3031 0.10003 0.09401 -0.0432 0.0254 1.0000
16.750 1.2975 0.10426 0.09832 -0.0441 0.0252 1.0000
17.000 1.2923 0.10847 0.10259 -0.0451 0.0251 1.0000
17.250 1.2856 0.11297 0.10717 -0.0463 0.0249 1.0000
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