GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 50,000 Max Cl/Cd: 38.57 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe144-il-50000.txt Download as CSV file: xf-goe144-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 144 (MVA H.21) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3361 0.11308 0.10610 -0.0216 1.0000 0.1440
-8.500 -0.3427 0.11247 0.10561 -0.0226 1.0000 0.1470
-8.250 -0.3569 0.11299 0.10629 -0.0234 1.0000 0.1479
-8.000 -0.3306 0.10514 0.09836 -0.0217 1.0000 0.1531
-7.750 -0.3297 0.10283 0.09614 -0.0213 1.0000 0.1576
-7.500 -0.3418 0.10240 0.09586 -0.0212 1.0000 0.1608
-7.250 -0.3573 0.10293 0.09657 -0.0233 1.0000 0.1620
-7.000 -0.3362 0.09594 0.08956 -0.0193 1.0000 0.1669
-6.750 -0.3367 0.09371 0.08742 -0.0190 1.0000 0.1724
-6.500 -0.3478 0.09388 0.08773 -0.0229 1.0000 0.1760
-6.250 -0.3361 0.08850 0.08239 -0.0186 1.0000 0.1813
-6.000 -0.3373 0.08686 0.08083 -0.0198 1.0000 0.1889
-5.500 -0.3315 0.08148 0.07558 -0.0198 1.0000 0.2034
-5.000 -0.3204 0.07678 0.07092 -0.0237 1.0000 0.2198
-4.750 -0.3158 0.07260 0.06684 -0.0196 1.0000 0.2244
-4.500 -0.3055 0.07022 0.06444 -0.0229 1.0000 0.2358
-4.250 -0.2940 0.06772 0.06189 -0.0247 1.0000 0.2494
-3.500 -0.2699 0.05874 0.05303 -0.0212 1.0000 0.2957
-3.250 -0.2569 0.05628 0.05055 -0.0224 1.0000 0.3212
-3.000 -0.2507 0.05353 0.04787 -0.0198 1.0000 0.3415
-2.750 -0.2448 0.05122 0.04561 -0.0180 1.0000 0.3807
-2.500 -0.2463 0.04908 0.04359 -0.0130 1.0000 0.4264
-2.250 -0.2463 0.04722 0.04178 -0.0085 1.0000 0.4805
-2.000 -0.0880 0.04050 0.03304 -0.0479 1.0000 0.2213
-1.750 -0.0623 0.03818 0.03045 -0.0494 1.0000 0.2139
-1.500 -0.0352 0.03620 0.02807 -0.0511 1.0000 0.2120
-1.250 -0.0088 0.03443 0.02586 -0.0524 1.0000 0.2122
-1.000 0.0135 0.03327 0.02438 -0.0530 1.0000 0.2241
-0.750 0.0529 0.03236 0.02315 -0.0565 0.9923 0.2539
-0.500 0.1040 0.03156 0.02204 -0.0620 0.9781 0.2858
-0.250 0.1551 0.03094 0.02103 -0.0671 0.9633 0.2985
0.000 0.2038 0.03055 0.02033 -0.0716 0.9484 0.3155
0.250 0.2558 0.03025 0.01969 -0.0765 0.9336 0.3307
0.500 0.3057 0.02985 0.01917 -0.0809 0.9192 0.3543
0.750 0.3523 0.02944 0.01882 -0.0846 0.9049 0.3935
1.000 0.3961 0.02892 0.01866 -0.0878 0.8906 0.4492
1.250 0.4413 0.02761 0.01860 -0.0909 0.8763 1.0000
1.500 0.4840 0.02810 0.01865 -0.0934 0.8610 1.0000
1.750 0.5253 0.02847 0.01873 -0.0955 0.8459 1.0000
2.000 0.5667 0.02870 0.01879 -0.0976 0.8309 1.0000
2.250 0.6097 0.02878 0.01875 -0.0996 0.8159 1.0000
2.500 0.6512 0.02874 0.01864 -0.1012 0.8009 1.0000
2.750 0.6857 0.02885 0.01872 -0.1016 0.7848 1.0000
3.000 0.7175 0.02903 0.01888 -0.1015 0.7685 1.0000
3.250 0.7510 0.02913 0.01899 -0.1016 0.7529 1.0000
3.500 0.7839 0.02926 0.01914 -0.1015 0.7374 1.0000
3.750 0.8158 0.02945 0.01940 -0.1013 0.7218 1.0000
4.000 0.8461 0.02975 0.01975 -0.1008 0.7061 1.0000
4.250 0.8756 0.03010 0.02015 -0.1002 0.6900 1.0000
4.500 0.9042 0.03052 0.02068 -0.0994 0.6739 1.0000
4.750 0.9325 0.03098 0.02122 -0.0986 0.6576 1.0000
5.000 0.9607 0.03146 0.02177 -0.0977 0.6413 1.0000
5.250 0.9830 0.03233 0.02275 -0.0963 0.6240 1.0000
5.500 1.0013 0.03344 0.02404 -0.0947 0.6058 1.0000
5.750 1.0251 0.03407 0.02478 -0.0931 0.5872 1.0000
6.000 1.0593 0.03358 0.02431 -0.0917 0.5668 1.0000
6.250 1.0775 0.03405 0.02490 -0.0892 0.5432 1.0000
6.500 1.1061 0.03380 0.02472 -0.0873 0.5213 1.0000
6.750 1.1252 0.03453 0.02562 -0.0853 0.5007 1.0000
7.000 1.1508 0.03486 0.02607 -0.0838 0.4817 1.0000
7.250 1.1720 0.03547 0.02684 -0.0819 0.4616 1.0000
7.500 1.1972 0.03452 0.02587 -0.0793 0.4331 1.0000
7.750 1.2174 0.03361 0.02500 -0.0764 0.4029 1.0000
8.000 1.2353 0.03298 0.02438 -0.0735 0.3747 1.0000
8.250 1.2525 0.03274 0.02419 -0.0708 0.3495 1.0000
8.500 1.2631 0.03275 0.02432 -0.0675 0.3217 1.0000
8.750 1.2691 0.03297 0.02461 -0.0637 0.2901 1.0000
9.000 1.2664 0.03362 0.02515 -0.0592 0.2497 1.0000
9.250 1.2577 0.03529 0.02671 -0.0545 0.2016 1.0000
9.500 1.2440 0.03776 0.02884 -0.0496 0.1569 1.0000
9.750 1.2325 0.04066 0.03135 -0.0455 0.1304 1.0000
10.000 1.2279 0.04364 0.03405 -0.0424 0.1142 1.0000
10.250 1.2350 0.04641 0.03675 -0.0401 0.1018 1.0000
10.500 1.2528 0.04912 0.03955 -0.0384 0.0919 1.0000
10.750 1.2745 0.05195 0.04234 -0.0374 0.0838 1.0000
11.000 1.2884 0.05486 0.04557 -0.0359 0.0787 1.0000
11.250 1.3120 0.05832 0.04918 -0.0354 0.0752 1.0000
11.500 1.3347 0.06307 0.05411 -0.0353 0.0732 1.0000
11.750 1.3305 0.06688 0.05836 -0.0331 0.0729 1.0000
12.000 1.3213 0.07092 0.06275 -0.0311 0.0728 1.0000
12.250 1.3090 0.07519 0.06733 -0.0296 0.0728 1.0000
12.500 1.2938 0.07980 0.07222 -0.0288 0.0730 1.0000
12.750 1.2766 0.08481 0.07748 -0.0288 0.0732 1.0000
13.250 1.2091 0.09768 0.09093 -0.0343 0.0751 1.0000
13.500 1.1293 0.11391 0.10750 -0.0473 0.0796 1.0000
13.750 1.0918 0.12709 0.12072 -0.0558 0.0828 1.0000
14.000 1.0736 0.13720 0.13080 -0.0613 0.0846 1.0000
14.250 1.0643 0.14563 0.13920 -0.0653 0.0856 1.0000
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Polar data table (+)
Polar graphs
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