GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 50,000 Max Cl/Cd: 29.19 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe147-il-50000.txt Download as CSV file: xf-goe147-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 147 (MVA H.6) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3773 0.12134 0.11498 0.0081 1.0000 0.1435
-9.500 -0.3833 0.11966 0.11335 0.0064 1.0000 0.1461
-9.250 -0.3945 0.11872 0.11249 0.0040 1.0000 0.1471
-9.000 -0.3696 0.11114 0.10491 0.0057 1.0000 0.1508
-8.750 -0.3639 0.10757 0.10137 0.0053 1.0000 0.1556
-8.500 -0.3688 0.10539 0.09925 0.0036 1.0000 0.1597
-8.250 -0.3813 0.10422 0.09818 0.0008 1.0000 0.1611
-8.000 -0.3552 0.09716 0.09110 0.0033 1.0000 0.1687
-7.750 -0.3600 0.09481 0.08883 0.0015 1.0000 0.1738
-7.500 -0.3745 0.09354 0.08770 -0.0017 1.0000 0.1753
-7.250 -0.3478 0.08667 0.08077 0.0012 1.0000 0.1833
-7.000 -0.3560 0.08448 0.07870 -0.0011 1.0000 0.1886
-6.750 -0.3522 0.08022 0.07450 -0.0019 1.0000 0.1918
-6.500 -0.3426 0.07612 0.07044 -0.0016 1.0000 0.1992
-6.250 -0.3461 0.07299 0.06741 -0.0072 1.0000 0.2047
-6.000 -0.3995 0.08214 0.07604 -0.0101 1.0000 0.2041
-5.750 -0.3868 0.07694 0.07092 -0.0053 1.0000 0.2099
-5.500 -0.3721 0.07335 0.06734 -0.0097 1.0000 0.2206
-5.250 -0.3562 0.06977 0.06376 -0.0124 1.0000 0.2342
-5.000 -0.3420 0.06605 0.06008 -0.0121 1.0000 0.2509
-4.750 -0.3242 0.06294 0.05694 -0.0156 1.0000 0.2763
-4.500 -0.3105 0.05905 0.05312 -0.0138 1.0000 0.2946
-4.250 -0.2945 0.05564 0.04971 -0.0143 1.0000 0.3227
-3.750 -0.1844 0.04270 0.03538 -0.0400 1.0000 0.1908
-3.500 -0.1540 0.03823 0.03062 -0.0420 1.0000 0.1838
-3.250 -0.1248 0.03494 0.02697 -0.0435 1.0000 0.1996
-3.000 -0.0977 0.03190 0.02365 -0.0442 1.0000 0.2244
-2.750 -0.0719 0.02950 0.02095 -0.0444 1.0000 0.2577
-2.500 -0.0496 0.02793 0.01924 -0.0440 1.0000 0.2917
-2.250 -0.0242 0.02661 0.01764 -0.0442 1.0000 0.3048
-2.000 -0.0021 0.02545 0.01641 -0.0439 1.0000 0.3138
-1.750 0.0212 0.02466 0.01538 -0.0440 1.0000 0.3151
-1.500 0.0426 0.02415 0.01466 -0.0440 1.0000 0.3165
-1.250 0.0624 0.02383 0.01419 -0.0441 1.0000 0.3212
-1.000 0.0818 0.02367 0.01396 -0.0444 1.0000 0.3254
-0.750 0.1023 0.02370 0.01387 -0.0451 1.0000 0.3278
-0.500 0.1508 0.02359 0.01349 -0.0504 0.9867 0.3324
-0.250 0.2232 0.02299 0.01275 -0.0590 0.9600 0.3427
0.000 0.2934 0.02224 0.01201 -0.0665 0.9335 0.3646
0.250 0.3525 0.02138 0.01130 -0.0714 0.9055 0.3926
0.500 0.3964 0.02036 0.01076 -0.0732 0.8759 0.4484
0.750 0.4316 0.01891 0.01030 -0.0719 0.8451 1.0000
1.000 0.4601 0.01920 0.01015 -0.0701 0.8128 1.0000
1.250 0.4845 0.01954 0.01020 -0.0677 0.7810 1.0000
1.500 0.5073 0.01991 0.01031 -0.0651 0.7494 1.0000
1.750 0.5298 0.02035 0.01056 -0.0628 0.7171 1.0000
2.000 0.5530 0.02086 0.01087 -0.0608 0.6857 1.0000
2.250 0.5766 0.02139 0.01121 -0.0590 0.6562 1.0000
2.500 0.6006 0.02196 0.01157 -0.0572 0.6298 1.0000
2.750 0.6250 0.02262 0.01212 -0.0560 0.6035 1.0000
3.000 0.6497 0.02335 0.01275 -0.0549 0.5790 1.0000
3.250 0.6744 0.02396 0.01320 -0.0536 0.5577 1.0000
3.500 0.6989 0.02470 0.01391 -0.0527 0.5342 1.0000
3.750 0.7236 0.02526 0.01435 -0.0514 0.5138 1.0000
4.000 0.7482 0.02601 0.01510 -0.0506 0.4926 1.0000
4.250 0.7730 0.02672 0.01578 -0.0497 0.4733 1.0000
4.500 0.7981 0.02742 0.01643 -0.0488 0.4560 1.0000
4.750 0.8232 0.02820 0.01721 -0.0480 0.4399 1.0000
5.000 0.8481 0.02909 0.01812 -0.0473 0.4240 1.0000
5.250 0.8728 0.03014 0.01925 -0.0468 0.4088 1.0000
5.500 0.8978 0.03125 0.02040 -0.0462 0.3961 1.0000
5.750 0.9215 0.03286 0.02227 -0.0461 0.3839 1.0000
6.000 0.9441 0.03483 0.02451 -0.0462 0.3734 1.0000
6.250 0.9684 0.03634 0.02609 -0.0457 0.3655 1.0000
6.500 0.9885 0.03882 0.02893 -0.0460 0.3568 1.0000
6.750 1.0104 0.04085 0.03113 -0.0459 0.3503 1.0000
7.000 1.0259 0.04423 0.03497 -0.0466 0.3438 1.0000
7.250 1.0455 0.04679 0.03775 -0.0467 0.3398 1.0000
7.500 1.0608 0.05038 0.04161 -0.0473 0.3373 1.0000
7.750 1.0593 0.05706 0.04874 -0.0500 0.3363 1.0000
8.000 1.0542 0.06422 0.05619 -0.0531 0.3371 1.0000
9.500 1.2280 0.05299 0.04574 -0.0359 0.2347 1.0000
9.750 1.2591 0.04469 0.03715 -0.0308 0.1756 1.0000
10.000 1.2654 0.04456 0.03668 -0.0280 0.1372 1.0000
10.250 1.2690 0.04738 0.03955 -0.0262 0.1193 1.0000
10.500 1.2726 0.05024 0.04247 -0.0246 0.1081 1.0000
10.750 1.2783 0.05254 0.04466 -0.0231 0.0993 1.0000
11.000 1.2707 0.05677 0.04935 -0.0221 0.0950 1.0000
11.250 1.2637 0.06029 0.05305 -0.0209 0.0916 1.0000
11.500 1.2694 0.06305 0.05575 -0.0196 0.0878 1.0000
11.750 1.2515 0.06836 0.06139 -0.0204 0.0874 1.0000
12.000 1.2305 0.07459 0.06788 -0.0227 0.0874 1.0000
12.250 1.2073 0.08179 0.07529 -0.0264 0.0878 1.0000
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Polar data table (+)
Polar graphs
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