GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il) Reynolds number: 200,000 Max Cl/Cd: 80.07 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe310-il-200000.txt Download as CSV file: xf-goe310-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 310 (MVA H.42) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2714 0.08940 0.08624 -0.0344 1.0000 0.0435
-8.500 -0.2889 0.08781 0.08473 -0.0344 1.0000 0.0441
-8.250 -0.3039 0.08613 0.08313 -0.0333 1.0000 0.0443
-8.000 -0.3204 0.08464 0.08170 -0.0316 1.0000 0.0444
-7.750 -0.2978 0.07989 0.07695 -0.0271 1.0000 0.0474
-7.500 -0.3072 0.07820 0.07532 -0.0249 1.0000 0.0481
-7.250 -0.3186 0.07660 0.07378 -0.0226 0.9999 0.0490
-7.000 -0.3084 0.07192 0.06910 -0.0281 0.9947 0.0521
-6.750 -0.2969 0.06504 0.06211 -0.0463 0.9839 0.0554
-6.500 -0.2831 0.06022 0.05735 -0.0430 0.9808 0.0575
-6.250 -0.2608 0.05682 0.05393 -0.0450 0.9751 0.0616
-6.000 -0.3236 0.06708 0.06393 -0.0436 0.9833 0.0583
-5.500 -0.1903 0.04124 0.03808 -0.0640 0.9569 0.0819
-5.250 -0.1675 0.03875 0.03558 -0.0646 0.9494 0.0878
-5.000 -0.1380 0.03367 0.03034 -0.0704 0.9442 0.0962
-4.750 -0.1058 0.02918 0.02559 -0.0761 0.9383 0.1082
-4.500 -0.1330 0.04431 0.04037 -0.0725 0.9441 0.1086
-4.250 -0.0974 0.04173 0.03778 -0.0750 0.9415 0.1129
-4.000 -0.0824 0.02472 0.01903 -0.0762 0.9296 0.0643
-3.750 -0.0444 0.02049 0.01368 -0.0774 0.9268 0.0561
-3.500 -0.0151 0.01929 0.01218 -0.0772 0.9174 0.0556
-3.250 0.0241 0.01725 0.00988 -0.0792 0.9133 0.0570
-3.000 0.0564 0.01617 0.00867 -0.0796 0.9044 0.0569
-2.750 0.0942 0.01510 0.00752 -0.0811 0.8982 0.0574
-2.500 0.1236 0.01436 0.00674 -0.0810 0.8873 0.0584
-2.250 0.1554 0.01375 0.00611 -0.0814 0.8775 0.0609
-2.000 0.1868 0.01325 0.00554 -0.0817 0.8670 0.0638
-1.750 0.2140 0.01288 0.00509 -0.0810 0.8534 0.0658
-1.500 0.2411 0.01254 0.00470 -0.0804 0.8398 0.0697
-1.250 0.2678 0.01215 0.00438 -0.0798 0.8260 0.0859
-1.000 0.2943 0.01187 0.00432 -0.0792 0.8120 0.1550
-0.750 0.3220 0.01190 0.00428 -0.0788 0.7983 0.1846
-0.500 0.3494 0.01195 0.00423 -0.0785 0.7850 0.2042
-0.250 0.3762 0.01194 0.00415 -0.0780 0.7722 0.2168
0.000 0.4031 0.01194 0.00408 -0.0776 0.7604 0.2316
0.250 0.4292 0.01191 0.00402 -0.0771 0.7486 0.2435
0.500 0.4543 0.01191 0.00400 -0.0765 0.7369 0.2562
0.750 0.4798 0.01191 0.00400 -0.0759 0.7264 0.2702
1.000 0.5059 0.01192 0.00403 -0.0755 0.7171 0.2938
1.250 0.5298 0.01191 0.00409 -0.0746 0.7059 0.3163
1.500 0.5536 0.01190 0.00413 -0.0737 0.6946 0.3415
1.750 0.5762 0.01179 0.00414 -0.0724 0.6824 0.3883
2.000 0.7172 0.01063 0.00410 -0.0968 0.6585 1.0000
2.250 0.7391 0.01076 0.00409 -0.0954 0.6427 1.0000
2.500 0.7610 0.01088 0.00412 -0.0939 0.6278 1.0000
2.750 0.7829 0.01101 0.00420 -0.0926 0.6146 1.0000
3.000 0.8054 0.01114 0.00430 -0.0914 0.6031 1.0000
3.250 0.8279 0.01128 0.00442 -0.0902 0.5917 1.0000
3.500 0.8504 0.01144 0.00452 -0.0891 0.5807 1.0000
3.750 0.8719 0.01157 0.00462 -0.0877 0.5668 1.0000
4.000 0.8937 0.01170 0.00478 -0.0863 0.5542 1.0000
4.250 0.9151 0.01184 0.00492 -0.0849 0.5404 1.0000
4.500 0.9362 0.01199 0.00506 -0.0835 0.5256 1.0000
4.750 0.9566 0.01215 0.00520 -0.0819 0.5084 1.0000
5.000 0.9767 0.01232 0.00538 -0.0803 0.4899 1.0000
5.250 0.9970 0.01249 0.00557 -0.0787 0.4712 1.0000
5.500 1.0167 0.01270 0.00577 -0.0770 0.4506 1.0000
5.750 1.0361 0.01294 0.00600 -0.0753 0.4274 1.0000
6.000 1.0535 0.01327 0.00625 -0.0732 0.3956 1.0000
6.250 1.0689 0.01371 0.00658 -0.0708 0.3594 1.0000
6.500 1.0830 0.01427 0.00698 -0.0683 0.3203 1.0000
6.750 1.0940 0.01502 0.00750 -0.0653 0.2749 1.0000
7.000 1.1036 0.01589 0.00812 -0.0621 0.2294 1.0000
7.250 1.1123 0.01684 0.00879 -0.0589 0.1831 1.0000
7.500 1.1207 0.01781 0.00953 -0.0556 0.1343 1.0000
7.750 1.1229 0.01915 0.01046 -0.0515 0.0810 1.0000
8.000 1.1287 0.02024 0.01145 -0.0479 0.0708 1.0000
8.250 1.1332 0.02123 0.01253 -0.0439 0.0651 1.0000
8.500 1.1297 0.02252 0.01388 -0.0388 0.0603 1.0000
8.750 1.1251 0.02402 0.01546 -0.0338 0.0559 1.0000
9.000 1.1239 0.02556 0.01705 -0.0297 0.0512 1.0000
9.250 1.1194 0.02819 0.01954 -0.0256 0.0470 1.0000
9.500 1.1306 0.02902 0.02057 -0.0234 0.0432 1.0000
9.750 1.1422 0.03048 0.02203 -0.0214 0.0398 1.0000
10.000 1.1706 0.03295 0.02436 -0.0216 0.0364 1.0000
10.250 1.1803 0.03383 0.02544 -0.0192 0.0345 1.0000
10.500 1.1922 0.03496 0.02669 -0.0173 0.0319 1.0000
10.750 1.2079 0.03640 0.02820 -0.0160 0.0303 1.0000
11.000 1.2566 0.04022 0.03201 -0.0193 0.0283 1.0000
11.250 1.2654 0.04186 0.03392 -0.0168 0.0278 1.0000
11.500 1.2730 0.04366 0.03598 -0.0143 0.0272 1.0000
11.750 1.2804 0.04590 0.03850 -0.0120 0.0265 1.0000
12.000 1.2814 0.04783 0.04067 -0.0093 0.0255 1.0000
12.250 1.2823 0.05010 0.04317 -0.0069 0.0249 1.0000
12.500 1.2805 0.05303 0.04637 -0.0044 0.0247 1.0000
12.750 1.2747 0.05622 0.04985 -0.0020 0.0249 1.0000
13.000 1.2644 0.05955 0.05346 0.0002 0.0249 1.0000
13.250 1.2516 0.06329 0.05746 0.0021 0.0252 1.0000
13.500 1.2366 0.06716 0.06157 0.0035 0.0253 1.0000
13.750 1.2199 0.07134 0.06599 0.0042 0.0255 1.0000
14.000 1.2020 0.07599 0.07085 0.0044 0.0260 1.0000
14.250 1.1822 0.08093 0.07600 0.0038 0.0262 1.0000
14.500 1.1612 0.08634 0.08160 0.0026 0.0264 1.0000
14.750 1.1415 0.09198 0.08741 0.0008 0.0267 1.0000
15.000 1.1203 0.09814 0.09373 -0.0016 0.0270 1.0000
15.250 1.1001 0.10472 0.10045 -0.0044 0.0273 1.0000
15.500 1.0786 0.11182 0.10768 -0.0081 0.0275 1.0000
15.750 1.0772 0.11669 0.11266 -0.0094 0.0293 1.0000
16.000 0.9982 0.13799 0.13432 -0.0264 0.0306 1.0000
16.250 0.7843 0.14243 0.13914 -0.0273 0.0360 1.0000
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Polar data table (+)
Polar graphs
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