GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il) Reynolds number: 500,000 Max Cl/Cd: 97.88 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe336-il-500000-n5.txt Download as CSV file: xf-goe336-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 336 (MVA H.44) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3049 0.08466 0.08236 -0.0377 0.8976 0.0127
-8.250 -0.3001 0.08246 0.07999 -0.0384 0.8465 0.0129
-8.000 -0.2944 0.08031 0.07764 -0.0395 0.7994 0.0131
-7.750 -0.2847 0.07778 0.07496 -0.0417 0.7698 0.0134
-7.500 -0.2730 0.07494 0.07200 -0.0445 0.7510 0.0138
-7.250 -0.2604 0.07149 0.06847 -0.0479 0.7376 0.0147
-7.000 -0.2519 0.06174 0.05858 -0.0576 0.7294 0.0164
-6.500 -0.2142 0.05752 0.05419 -0.0612 0.7101 0.0170
-6.250 -0.1940 0.05554 0.05212 -0.0628 0.7016 0.0176
-6.000 -0.1730 0.05259 0.04908 -0.0652 0.6933 0.0185
-5.750 -0.1513 0.04746 0.04376 -0.0687 0.6862 0.0197
-5.500 -0.1299 0.03943 0.03542 -0.0726 0.6798 0.0216
-5.250 -0.1070 0.03814 0.03401 -0.0730 0.6711 0.0221
-5.000 -0.0835 0.03641 0.03217 -0.0735 0.6622 0.0225
-4.750 -0.0602 0.03370 0.02928 -0.0741 0.6542 0.0231
-4.500 -0.0369 0.03015 0.02548 -0.0744 0.6460 0.0239
-4.250 -0.0193 0.02136 0.01593 -0.0737 0.6403 0.0257
-4.000 0.0031 0.01831 0.01236 -0.0729 0.6314 0.0261
-3.750 0.0280 0.01687 0.01059 -0.0724 0.6220 0.0264
-3.500 0.0538 0.01596 0.00941 -0.0720 0.6115 0.0268
-3.250 0.0804 0.01539 0.00865 -0.0717 0.6002 0.0272
-3.000 0.1069 0.01477 0.00783 -0.0714 0.5890 0.0274
-2.750 0.1335 0.01422 0.00708 -0.0711 0.5776 0.0275
-2.500 0.1595 0.01323 0.00584 -0.0707 0.5666 0.0279
-2.250 0.1860 0.01253 0.00499 -0.0703 0.5565 0.0285
-2.000 0.2128 0.01209 0.00442 -0.0701 0.5476 0.0290
-1.750 0.2397 0.01176 0.00400 -0.0698 0.5388 0.0294
-1.500 0.2666 0.01149 0.00366 -0.0696 0.5312 0.0298
-1.250 0.2936 0.01127 0.00337 -0.0693 0.5237 0.0302
-1.000 0.3205 0.01108 0.00313 -0.0691 0.5173 0.0306
-0.750 0.3476 0.01091 0.00293 -0.0688 0.5109 0.0310
-0.500 0.3745 0.01080 0.00276 -0.0686 0.5050 0.0318
-0.250 0.4017 0.01068 0.00262 -0.0684 0.4997 0.0326
0.000 0.4287 0.01058 0.00248 -0.0682 0.4939 0.0330
0.250 0.4556 0.01052 0.00237 -0.0679 0.4871 0.0336
0.500 0.4826 0.01047 0.00228 -0.0677 0.4789 0.0343
0.750 0.5094 0.01046 0.00221 -0.0674 0.4719 0.0351
1.000 0.5367 0.01042 0.00216 -0.0673 0.4664 0.0360
1.250 0.5639 0.01041 0.00213 -0.0671 0.4619 0.0383
1.500 0.5907 0.01041 0.00212 -0.0669 0.4565 0.0431
1.750 0.6175 0.01035 0.00217 -0.0667 0.4496 0.0729
2.000 0.6442 0.01041 0.00222 -0.0665 0.4420 0.0864
2.250 0.6714 0.01043 0.00227 -0.0664 0.4358 0.0982
2.500 0.6984 0.01045 0.00233 -0.0662 0.4308 0.1123
3.000 0.7522 0.01051 0.00248 -0.0659 0.4216 0.1432
3.250 0.7784 0.01047 0.00259 -0.0657 0.4147 0.2117
3.500 0.7903 0.00915 0.00270 -0.0627 0.4097 0.8390
4.000 0.9165 0.00949 0.00317 -0.0788 0.3807 1.0000
4.250 0.9410 0.00966 0.00328 -0.0782 0.3659 1.0000
4.500 0.9651 0.00986 0.00340 -0.0775 0.3453 1.0000
4.750 0.9853 0.01042 0.00366 -0.0763 0.2861 1.0000
5.000 1.0031 0.01123 0.00415 -0.0748 0.2301 1.0000
5.250 1.0242 0.01169 0.00449 -0.0737 0.2077 1.0000
5.500 1.0444 0.01223 0.00487 -0.0725 0.1787 1.0000
5.750 1.0608 0.01307 0.00540 -0.0707 0.1270 1.0000
6.000 1.0804 0.01359 0.00581 -0.0694 0.1074 1.0000
6.250 1.1003 0.01406 0.00620 -0.0682 0.0894 1.0000
6.500 1.1172 0.01475 0.00671 -0.0664 0.0620 1.0000
6.750 1.1372 0.01517 0.00711 -0.0652 0.0548 1.0000
7.000 1.1578 0.01552 0.00748 -0.0640 0.0514 1.0000
7.250 1.1772 0.01595 0.00791 -0.0627 0.0473 1.0000
7.500 1.1968 0.01633 0.00831 -0.0614 0.0431 1.0000
7.750 1.2129 0.01694 0.00882 -0.0596 0.0222 1.0000
8.000 1.2273 0.01764 0.00950 -0.0575 0.0149 1.0000
8.250 1.2435 0.01820 0.01012 -0.0556 0.0131 1.0000
8.500 1.2601 0.01871 0.01069 -0.0539 0.0121 1.0000
8.750 1.2756 0.01926 0.01130 -0.0520 0.0111 1.0000
9.000 1.2892 0.01987 0.01199 -0.0499 0.0104 1.0000
9.250 1.2988 0.02056 0.01276 -0.0470 0.0099 1.0000
9.500 1.3062 0.02141 0.01370 -0.0440 0.0093 1.0000
9.750 1.3174 0.02213 0.01449 -0.0418 0.0090 1.0000
10.000 1.3280 0.02297 0.01540 -0.0397 0.0087 1.0000
10.250 1.3378 0.02391 0.01642 -0.0377 0.0082 1.0000
10.500 1.3471 0.02497 0.01756 -0.0359 0.0078 1.0000
10.750 1.3555 0.02618 0.01884 -0.0342 0.0074 1.0000
11.000 1.3622 0.02761 0.02036 -0.0326 0.0072 1.0000
11.250 1.3660 0.02940 0.02224 -0.0311 0.0069 1.0000
11.500 1.3683 0.03149 0.02442 -0.0299 0.0068 1.0000
11.750 1.3737 0.03341 0.02643 -0.0290 0.0066 1.0000
12.000 1.3778 0.03554 0.02866 -0.0284 0.0065 1.0000
12.250 1.3804 0.03789 0.03111 -0.0278 0.0063 1.0000
12.500 1.3817 0.04043 0.03375 -0.0272 0.0062 1.0000
12.750 1.3821 0.04312 0.03654 -0.0268 0.0060 1.0000
13.000 1.3812 0.04599 0.03950 -0.0265 0.0059 1.0000
13.250 1.3796 0.04899 0.04262 -0.0263 0.0058 1.0000
13.500 1.3778 0.05207 0.04579 -0.0262 0.0056 1.0000
13.750 1.3756 0.05524 0.04906 -0.0262 0.0055 1.0000
14.000 1.3733 0.05852 0.05243 -0.0263 0.0054 1.0000
14.250 1.3709 0.06189 0.05589 -0.0265 0.0053 1.0000
14.500 1.3674 0.06544 0.05953 -0.0269 0.0052 1.0000
14.750 1.3636 0.06913 0.06330 -0.0273 0.0051 1.0000
15.000 1.3585 0.07309 0.06735 -0.0279 0.0050 1.0000
15.250 1.3510 0.07739 0.07174 -0.0286 0.0049 1.0000
15.500 1.3423 0.08192 0.07636 -0.0294 0.0048 1.0000
15.750 1.3387 0.08585 0.08039 -0.0302 0.0047 1.0000
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Polar data table (+)
Polar graphs
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