GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.16 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe309-il-1000000-n5.txt Download as CSV file: xf-goe309-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 309 (MVA H.41) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3915 0.09496 0.09331 -0.0126 0.8914 0.0037
-8.500 -0.3915 0.09123 0.08942 -0.0139 0.8476 0.0038
-7.500 -0.4693 0.01789 0.01367 -0.0526 0.7876 0.0047
-7.250 -0.4462 0.01583 0.01122 -0.0523 0.7735 0.0050
-7.000 -0.4210 0.01462 0.00977 -0.0521 0.7623 0.0054
-6.500 -0.3682 0.01310 0.00791 -0.0518 0.7422 0.0060
-6.250 -0.3412 0.01251 0.00716 -0.0517 0.7336 0.0065
-6.000 -0.3140 0.01200 0.00650 -0.0516 0.7246 0.0068
-5.750 -0.2866 0.01152 0.00588 -0.0515 0.7167 0.0073
-5.500 -0.2593 0.01102 0.00528 -0.0514 0.7090 0.0084
-5.250 -0.2317 0.01063 0.00479 -0.0513 0.7014 0.0095
-5.000 -0.2040 0.01031 0.00436 -0.0513 0.6934 0.0111
-4.750 -0.1760 0.01013 0.00421 -0.0513 0.6858 0.0138
-4.500 -0.1479 0.01000 0.00405 -0.0513 0.6785 0.0159
-4.250 -0.1192 0.01006 0.00414 -0.0515 0.6710 0.0181
-4.000 -0.0907 0.01011 0.00416 -0.0515 0.6627 0.0203
-3.750 -0.0622 0.01014 0.00415 -0.0517 0.6540 0.0221
-3.500 -0.0337 0.01017 0.00414 -0.0518 0.6458 0.0231
-3.250 -0.0052 0.01022 0.00415 -0.0519 0.6371 0.0237
-3.000 0.0233 0.01030 0.00420 -0.0520 0.6284 0.0241
-2.750 0.0506 0.00978 0.00354 -0.0519 0.6186 0.0253
-2.500 0.0782 0.00941 0.00308 -0.0519 0.6078 0.0265
-2.250 0.1060 0.00919 0.00280 -0.0519 0.5976 0.0272
-2.000 0.1339 0.00901 0.00253 -0.0518 0.5873 0.0275
-1.750 0.1618 0.00886 0.00230 -0.0518 0.5762 0.0276
-1.500 0.1898 0.00873 0.00211 -0.0519 0.5642 0.0281
-1.250 0.2178 0.00862 0.00193 -0.0519 0.5518 0.0284
-1.000 0.2456 0.00855 0.00177 -0.0519 0.5365 0.0284
-0.750 0.2734 0.00853 0.00164 -0.0519 0.5185 0.0285
-0.500 0.3013 0.00851 0.00153 -0.0519 0.5019 0.0288
0.000 0.3573 0.00848 0.00137 -0.0521 0.4760 0.0302
0.250 0.3853 0.00848 0.00133 -0.0522 0.4634 0.0319
0.500 0.4133 0.00851 0.00130 -0.0522 0.4509 0.0344
0.750 0.4412 0.00855 0.00129 -0.0523 0.4367 0.0396
1.000 0.4688 0.00853 0.00131 -0.0524 0.4230 0.0681
1.250 0.4968 0.00856 0.00136 -0.0525 0.4136 0.0885
1.500 0.5249 0.00858 0.00139 -0.0527 0.4067 0.0968
1.750 0.5529 0.00863 0.00142 -0.0528 0.4000 0.1017
2.000 0.5811 0.00866 0.00145 -0.0530 0.3935 0.1081
2.500 0.6371 0.00874 0.00155 -0.0532 0.3797 0.1225
2.750 0.6648 0.00874 0.00162 -0.0534 0.3720 0.1618
3.000 0.6919 0.00853 0.00177 -0.0535 0.3647 0.3342
3.500 0.7319 0.00724 0.00201 -0.0504 0.3486 0.9568
3.750 0.7597 0.00751 0.00215 -0.0506 0.3181 0.9731
4.000 0.7898 0.00789 0.00234 -0.0514 0.2800 0.9844
4.250 0.8203 0.00835 0.00259 -0.0525 0.2390 0.9904
4.500 0.8487 0.00890 0.00290 -0.0532 0.1955 0.9949
4.750 0.8797 0.00933 0.00317 -0.0543 0.1684 0.9977
5.000 0.9093 0.00976 0.00345 -0.0552 0.1426 1.0000
5.250 0.9274 0.01072 0.00402 -0.0539 0.0716 1.0000
5.500 0.9472 0.01154 0.00461 -0.0527 0.0173 1.0000
5.750 0.9719 0.01177 0.00486 -0.0523 0.0130 1.0000
6.000 0.9968 0.01202 0.00513 -0.0520 0.0116 1.0000
6.250 1.0215 0.01229 0.00543 -0.0516 0.0100 1.0000
6.500 1.0458 0.01263 0.00580 -0.0512 0.0086 1.0000
6.750 1.0699 0.01298 0.00620 -0.0507 0.0077 1.0000
7.000 1.0942 0.01330 0.00654 -0.0504 0.0070 1.0000
7.250 1.1183 0.01364 0.00690 -0.0500 0.0062 1.0000
7.500 1.1414 0.01409 0.00736 -0.0495 0.0055 1.0000
7.750 1.1642 0.01456 0.00788 -0.0489 0.0052 1.0000
8.000 1.1870 0.01500 0.00838 -0.0483 0.0048 1.0000
8.250 1.2093 0.01548 0.00891 -0.0477 0.0045 1.0000
8.500 1.2311 0.01597 0.00944 -0.0470 0.0042 1.0000
8.750 1.2529 0.01645 0.00994 -0.0464 0.0039 1.0000
9.000 1.2723 0.01712 0.01066 -0.0454 0.0035 1.0000
9.250 1.2915 0.01777 0.01137 -0.0444 0.0033 1.0000
9.500 1.3100 0.01844 0.01211 -0.0433 0.0032 1.0000
9.750 1.3269 0.01918 0.01295 -0.0419 0.0031 1.0000
10.000 1.3423 0.01998 0.01383 -0.0404 0.0029 1.0000
10.250 1.3553 0.02081 0.01474 -0.0386 0.0028 1.0000
10.500 1.3646 0.02170 0.01570 -0.0361 0.0027 1.0000
10.750 1.3738 0.02265 0.01672 -0.0340 0.0026 1.0000
11.000 1.3830 0.02368 0.01783 -0.0320 0.0025 1.0000
11.250 1.3912 0.02488 0.01910 -0.0302 0.0024 1.0000
11.500 1.3989 0.02618 0.02048 -0.0287 0.0023 1.0000
11.750 1.4050 0.02772 0.02210 -0.0273 0.0023 1.0000
12.000 1.4069 0.02978 0.02426 -0.0260 0.0022 1.0000
12.250 1.4030 0.03256 0.02717 -0.0248 0.0021 1.0000
12.500 1.3988 0.03559 0.03033 -0.0240 0.0021 1.0000
12.750 1.3983 0.03836 0.03321 -0.0236 0.0021 1.0000
13.000 1.3963 0.04139 0.03639 -0.0233 0.0020 1.0000
13.250 1.3928 0.04466 0.03977 -0.0232 0.0020 1.0000
13.500 1.3890 0.04806 0.04330 -0.0233 0.0020 1.0000
13.750 1.3835 0.05170 0.04705 -0.0234 0.0019 1.0000
14.000 1.3781 0.05542 0.05089 -0.0236 0.0019 1.0000
14.250 1.3719 0.05933 0.05491 -0.0241 0.0019 1.0000
14.500 1.3652 0.06339 0.05909 -0.0246 0.0018 1.0000
14.750 1.3592 0.06749 0.06331 -0.0253 0.0018 1.0000
15.000 1.3525 0.07176 0.06769 -0.0260 0.0017 1.0000
15.250 1.3451 0.07617 0.07222 -0.0268 0.0017 1.0000
15.500 1.3381 0.08063 0.07680 -0.0278 0.0016 1.0000
15.750 1.3304 0.08527 0.08155 -0.0288 0.0016 1.0000
16.000 1.3212 0.09010 0.08651 -0.0298 0.0016 1.0000
16.250 1.3117 0.09510 0.09164 -0.0310 0.0015 1.0000
16.500 1.3017 0.10030 0.09698 -0.0323 0.0015 1.0000
16.750 1.2896 0.10582 0.10264 -0.0336 0.0015 1.0000
17.000 1.2777 0.11158 0.10855 -0.0354 0.0014 1.0000
17.250 1.2649 0.11779 0.11490 -0.0378 0.0014 1.0000
17.500 1.2526 0.12419 0.12143 -0.0405 0.0014 1.0000
17.750 1.2394 0.13092 0.12830 -0.0437 0.0014 1.0000
18.000 1.2252 0.13814 0.13565 -0.0473 0.0014 1.0000
18.250 1.2115 0.14557 0.14322 -0.0512 0.0014 1.0000
18.500 1.1981 0.15326 0.15103 -0.0555 0.0014 1.0000
18.750 1.1829 0.16172 0.15963 -0.0604 0.0014 1.0000
19.000 1.1673 0.17064 0.16868 -0.0657 0.0014 1.0000
19.250 1.1532 0.17965 0.17781 -0.0712 0.0014 1.0000
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