GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.58 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe239-il-1000000-n5.txt Download as CSV file: xf-goe239-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 239 (MVA H.31) 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7900 0.02776 0.02489 -0.1315 0.9619 0.0124
-13.000 -0.7611 0.02324 0.02009 -0.1385 0.9483 0.0130
-12.500 -0.7078 0.02029 0.01680 -0.1421 0.9231 0.0142
-12.250 -0.6819 0.01927 0.01562 -0.1430 0.9129 0.0148
-11.750 -0.6290 0.01777 0.01391 -0.1441 0.8960 0.0161
-11.500 -0.6020 0.01721 0.01326 -0.1444 0.8895 0.0168
-11.250 -0.5747 0.01665 0.01260 -0.1448 0.8843 0.0174
-11.000 -0.5472 0.01609 0.01193 -0.1452 0.8791 0.0180
-10.750 -0.5197 0.01557 0.01129 -0.1455 0.8733 0.0184
-10.500 -0.4921 0.01505 0.01068 -0.1459 0.8683 0.0190
-10.250 -0.4639 0.01469 0.01028 -0.1461 0.8636 0.0196
-10.000 -0.4357 0.01439 0.00994 -0.1463 0.8590 0.0202
-9.500 -0.3792 0.01376 0.00915 -0.1467 0.8482 0.0214
-9.250 -0.3509 0.01340 0.00870 -0.1470 0.8426 0.0219
-9.000 -0.3226 0.01310 0.00829 -0.1471 0.8373 0.0223
-8.750 -0.2940 0.01274 0.00785 -0.1474 0.8319 0.0227
-8.500 -0.2655 0.01231 0.00736 -0.1477 0.8257 0.0234
-8.250 -0.2370 0.01202 0.00701 -0.1479 0.8193 0.0239
-8.000 -0.2083 0.01179 0.00673 -0.1480 0.8118 0.0244
-7.750 -0.1797 0.01156 0.00643 -0.1482 0.8050 0.0250
-7.500 -0.1507 0.01130 0.00611 -0.1484 0.7987 0.0256
-7.250 -0.1220 0.01108 0.00580 -0.1485 0.7909 0.0261
-7.000 -0.0931 0.01082 0.00547 -0.1487 0.7825 0.0266
-6.750 -0.0644 0.01062 0.00517 -0.1488 0.7726 0.0269
-6.500 -0.0355 0.01044 0.00491 -0.1490 0.7615 0.0272
-6.250 -0.0067 0.01006 0.00443 -0.1492 0.7489 0.0279
-6.000 0.0220 0.00982 0.00410 -0.1493 0.7321 0.0285
-5.750 0.0502 0.00969 0.00384 -0.1494 0.7081 0.0290
-5.500 0.0779 0.00965 0.00362 -0.1493 0.6709 0.0296
-5.250 0.1051 0.00969 0.00346 -0.1491 0.6281 0.0302
-5.000 0.1328 0.00971 0.00331 -0.1490 0.5955 0.0308
-4.750 0.1612 0.00967 0.00314 -0.1491 0.5752 0.0314
-4.500 0.1899 0.00960 0.00299 -0.1492 0.5622 0.0319
-4.250 0.2187 0.00953 0.00284 -0.1493 0.5520 0.0324
-4.000 0.2475 0.00946 0.00270 -0.1494 0.5440 0.0328
-3.750 0.2766 0.00934 0.00252 -0.1496 0.5366 0.0341
-3.500 0.3055 0.00926 0.00241 -0.1497 0.5308 0.0353
-3.250 0.3346 0.00918 0.00230 -0.1498 0.5261 0.0366
-3.000 0.3635 0.00913 0.00222 -0.1500 0.5212 0.0382
-2.500 0.4214 0.00902 0.00207 -0.1502 0.5128 0.0429
-2.250 0.4505 0.00896 0.00201 -0.1504 0.5089 0.0464
-2.000 0.4793 0.00892 0.00196 -0.1505 0.5042 0.0512
-1.750 0.5080 0.00891 0.00193 -0.1505 0.4992 0.0571
-1.500 0.5370 0.00885 0.00190 -0.1507 0.4956 0.0662
-1.250 0.5659 0.00880 0.00187 -0.1508 0.4913 0.0774
-1.000 0.5946 0.00878 0.00186 -0.1509 0.4855 0.0901
-0.750 0.6232 0.00876 0.00184 -0.1510 0.4799 0.1033
-0.500 0.6522 0.00867 0.00182 -0.1513 0.4753 0.1296
-0.250 0.6811 0.00856 0.00186 -0.1515 0.4718 0.1903
0.000 0.7096 0.00859 0.00189 -0.1516 0.4681 0.2032
0.250 0.7381 0.00861 0.00192 -0.1516 0.4644 0.2169
0.500 0.7669 0.00861 0.00196 -0.1517 0.4611 0.2276
0.750 0.7955 0.00863 0.00199 -0.1518 0.4575 0.2365
1.000 0.8239 0.00866 0.00204 -0.1519 0.4537 0.2477
1.250 0.8521 0.00870 0.00210 -0.1519 0.4499 0.2581
1.500 0.8806 0.00873 0.00215 -0.1520 0.4466 0.2683
2.000 0.9373 0.00881 0.00229 -0.1521 0.4379 0.2958
2.250 0.9652 0.00888 0.00237 -0.1521 0.4331 0.3093
2.500 0.9934 0.00892 0.00246 -0.1521 0.4280 0.3268
2.750 1.0212 0.00900 0.00255 -0.1521 0.4198 0.3433
3.000 1.0488 0.00909 0.00264 -0.1521 0.4108 0.3547
3.250 1.0760 0.00922 0.00275 -0.1519 0.3995 0.3643
3.500 1.1029 0.00938 0.00287 -0.1518 0.3860 0.3745
3.750 1.1288 0.00962 0.00303 -0.1515 0.3635 0.3839
4.250 1.1798 0.01017 0.00343 -0.1507 0.3255 0.4048
4.500 1.2061 0.01036 0.00362 -0.1505 0.3137 0.4180
4.750 1.2322 0.01055 0.00382 -0.1502 0.3028 0.4371
5.000 1.2582 0.01071 0.00406 -0.1501 0.2905 0.5032
5.250 1.2784 0.01018 0.00437 -0.1487 0.2789 1.0000
5.500 1.3043 0.01041 0.00457 -0.1484 0.2696 1.0000
5.750 1.3298 0.01067 0.00479 -0.1480 0.2611 1.0000
6.000 1.3553 0.01091 0.00501 -0.1476 0.2528 1.0000
6.250 1.3805 0.01117 0.00525 -0.1472 0.2453 1.0000
6.500 1.4056 0.01143 0.00548 -0.1468 0.2373 1.0000
6.750 1.4301 0.01173 0.00575 -0.1463 0.2284 1.0000
7.250 1.4762 0.01254 0.00641 -0.1449 0.2004 1.0000
7.500 1.4973 0.01307 0.00682 -0.1438 0.1779 1.0000
7.750 1.5084 0.01434 0.00772 -0.1413 0.1216 1.0000
8.000 1.5266 0.01501 0.00830 -0.1397 0.1039 1.0000
8.250 1.5415 0.01588 0.00902 -0.1377 0.0769 1.0000
8.500 1.5558 0.01671 0.00972 -0.1356 0.0576 1.0000
8.750 1.5741 0.01719 0.01020 -0.1341 0.0536 1.0000
9.000 1.5907 0.01771 0.01072 -0.1323 0.0494 1.0000
9.250 1.6072 0.01815 0.01120 -0.1304 0.0472 1.0000
9.500 1.6227 0.01867 0.01173 -0.1285 0.0444 1.0000
9.750 1.6368 0.01929 0.01236 -0.1263 0.0415 1.0000
10.000 1.6516 0.01988 0.01298 -0.1244 0.0391 1.0000
10.250 1.6663 0.02050 0.01362 -0.1226 0.0363 1.0000
10.500 1.6782 0.02131 0.01443 -0.1204 0.0326 1.0000
10.750 1.6910 0.02209 0.01523 -0.1185 0.0288 1.0000
11.000 1.7002 0.02314 0.01626 -0.1162 0.0229 1.0000
11.250 1.7074 0.02437 0.01747 -0.1138 0.0176 1.0000
11.500 1.7159 0.02557 0.01869 -0.1117 0.0152 1.0000
11.750 1.7246 0.02679 0.01996 -0.1098 0.0136 1.0000
12.000 1.7329 0.02810 0.02131 -0.1079 0.0124 1.0000
12.250 1.7400 0.02954 0.02281 -0.1060 0.0114 1.0000
12.500 1.7476 0.03099 0.02431 -0.1044 0.0108 1.0000
12.750 1.7549 0.03251 0.02589 -0.1028 0.0103 1.0000
13.000 1.7608 0.03420 0.02765 -0.1012 0.0098 1.0000
13.250 1.7650 0.03609 0.02960 -0.0996 0.0093 1.0000
13.500 1.7679 0.03816 0.03175 -0.0982 0.0089 1.0000
13.750 1.7694 0.04047 0.03413 -0.0968 0.0085 1.0000
14.000 1.7724 0.04268 0.03642 -0.0956 0.0083 1.0000
14.250 1.7741 0.04511 0.03894 -0.0946 0.0080 1.0000
14.500 1.7748 0.04779 0.04169 -0.0938 0.0078 1.0000
14.750 1.7743 0.05069 0.04468 -0.0931 0.0075 1.0000
15.000 1.7730 0.05381 0.04789 -0.0926 0.0073 1.0000
15.250 1.7701 0.05721 0.05137 -0.0922 0.0070 1.0000
15.500 1.7662 0.06085 0.05510 -0.0920 0.0068 1.0000
15.750 1.7608 0.06477 0.05911 -0.0920 0.0066 1.0000
16.000 1.7543 0.06887 0.06330 -0.0921 0.0064 1.0000
16.250 1.7493 0.07278 0.06731 -0.0922 0.0063 1.0000
16.500 1.7436 0.07682 0.07145 -0.0925 0.0062 1.0000
16.750 1.7371 0.08100 0.07573 -0.0928 0.0061 1.0000
17.000 1.7300 0.08528 0.08010 -0.0932 0.0060 1.0000
17.250 1.7222 0.08966 0.08458 -0.0936 0.0059 1.0000
17.500 1.7139 0.09419 0.08920 -0.0942 0.0058 1.0000
17.750 1.7055 0.09878 0.09389 -0.0949 0.0057 1.0000
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