GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 429 AIRFOIL (goe429-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.91 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe429-il-1000000.txt Download as CSV file: xf-goe429-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 429 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.3341 0.08870 0.08537 0.0242 1.0000 0.0102
-16.750 -1.3578 0.08092 0.07746 0.0203 1.0000 0.0103
-16.500 -1.3802 0.07357 0.06998 0.0166 1.0000 0.0103
-16.250 -1.4019 0.06647 0.06276 0.0131 1.0000 0.0103
-16.000 -1.4206 0.05991 0.05606 0.0097 1.0000 0.0103
-15.750 -1.4371 0.05375 0.04977 0.0065 1.0000 0.0103
-15.500 -1.4500 0.04825 0.04414 0.0036 1.0000 0.0104
-15.250 -1.4588 0.04349 0.03926 0.0012 1.0000 0.0105
-15.000 -1.4636 0.03947 0.03512 -0.0008 1.0000 0.0106
-14.750 -1.4648 0.03604 0.03158 -0.0024 1.0000 0.0107
-14.500 -1.4632 0.03308 0.02852 -0.0037 1.0000 0.0109
-14.250 -1.4601 0.03056 0.02588 -0.0046 1.0000 0.0111
-14.000 -1.4566 0.02865 0.02388 -0.0041 1.0000 0.0112
-13.750 -1.4492 0.02726 0.02239 -0.0028 1.0000 0.0114
-13.500 -1.4357 0.02607 0.02111 -0.0021 1.0000 0.0117
-13.250 -1.4195 0.02503 0.02000 -0.0014 1.0000 0.0120
-13.000 -1.4010 0.02416 0.01904 -0.0008 1.0000 0.0122
-12.750 -1.3833 0.02313 0.01792 -0.0002 1.0000 0.0125
-12.500 -1.3680 0.02168 0.01638 0.0006 1.0000 0.0131
-12.250 -1.3481 0.02072 0.01536 0.0011 1.0000 0.0135
-12.000 -1.3264 0.01993 0.01452 0.0016 1.0000 0.0140
-11.750 -1.3038 0.01922 0.01374 0.0019 1.0000 0.0145
-11.500 -1.2804 0.01856 0.01303 0.0023 1.0000 0.0149
-11.250 -1.2562 0.01799 0.01239 0.0026 1.0000 0.0153
-11.000 -1.2340 0.01703 0.01138 0.0030 1.0000 0.0163
-10.750 -1.2097 0.01638 0.01069 0.0032 1.0000 0.0173
-10.500 -1.1846 0.01584 0.01011 0.0034 1.0000 0.0182
-10.250 -1.1595 0.01523 0.00946 0.0036 1.0000 0.0196
-10.000 -1.1342 0.01463 0.00885 0.0038 1.0000 0.0215
-9.750 -1.1086 0.01406 0.00827 0.0040 1.0000 0.0242
-9.500 -1.0827 0.01348 0.00771 0.0041 1.0000 0.0287
-9.250 -1.0567 0.01293 0.00720 0.0042 1.0000 0.0354
-9.000 -1.0300 0.01248 0.00680 0.0042 1.0000 0.0419
-8.750 -1.0027 0.01214 0.00647 0.0042 1.0000 0.0470
-8.500 -0.9753 0.01179 0.00615 0.0042 1.0000 0.0522
-8.250 -0.9476 0.01150 0.00586 0.0042 1.0000 0.0561
-8.000 -0.9198 0.01119 0.00559 0.0042 1.0000 0.0606
-7.750 -0.8916 0.01099 0.00536 0.0041 1.0000 0.0634
-7.500 -0.8636 0.01066 0.00506 0.0040 1.0000 0.0682
-7.250 -0.8353 0.01042 0.00483 0.0040 1.0000 0.0722
-7.000 -0.8067 0.01024 0.00463 0.0039 1.0000 0.0748
-6.750 -0.7784 0.00992 0.00434 0.0037 1.0000 0.0802
-6.500 -0.7498 0.00969 0.00413 0.0036 1.0000 0.0844
-6.250 -0.7210 0.00948 0.00392 0.0035 1.0000 0.0889
-6.000 -0.6923 0.00920 0.00368 0.0033 1.0000 0.0956
-5.750 -0.6632 0.00902 0.00350 0.0031 1.0000 0.1001
-5.500 -0.6343 0.00870 0.00324 0.0029 1.0000 0.1089
-5.250 -0.6041 0.00852 0.00306 0.0025 0.9473 0.1185
-5.000 -0.5812 0.00831 0.00286 0.0038 0.9089 0.1379
-4.750 -0.5559 0.00799 0.00266 0.0043 0.8785 0.1820
-4.500 -0.5289 0.00785 0.00250 0.0047 0.8490 0.2023
-4.250 -0.5010 0.00774 0.00236 0.0048 0.8231 0.2173
-3.750 -0.4441 0.00752 0.00208 0.0049 0.7821 0.2455
-3.500 -0.4153 0.00740 0.00196 0.0048 0.7660 0.2605
-3.250 -0.3865 0.00727 0.00185 0.0047 0.7503 0.2804
-3.000 -0.3576 0.00712 0.00174 0.0046 0.7348 0.3050
-2.750 -0.3286 0.00697 0.00164 0.0045 0.7225 0.3311
-2.500 -0.2996 0.00684 0.00157 0.0044 0.7123 0.3589
-2.250 -0.2703 0.00671 0.00150 0.0042 0.7023 0.3841
-2.000 -0.2411 0.00663 0.00145 0.0041 0.6923 0.4035
-1.750 -0.2118 0.00655 0.00140 0.0040 0.6820 0.4232
-1.500 -0.1825 0.00646 0.00135 0.0038 0.6687 0.4446
-1.250 -0.1532 0.00640 0.00131 0.0037 0.6534 0.4623
-1.000 -0.1238 0.00635 0.00127 0.0036 0.6392 0.4778
-0.750 -0.0944 0.00630 0.00124 0.0035 0.6260 0.4958
-0.500 -0.0650 0.00625 0.00121 0.0033 0.6114 0.5145
-0.250 -0.0356 0.00620 0.00119 0.0032 0.5941 0.5361
0.000 -0.0063 0.00617 0.00118 0.0030 0.5729 0.5590
0.250 0.0231 0.00619 0.00118 0.0029 0.5463 0.5787
0.500 0.0525 0.00626 0.00120 0.0027 0.5101 0.5984
0.750 0.0818 0.00640 0.00124 0.0025 0.4661 0.6165
1.000 0.1111 0.00657 0.00129 0.0023 0.4235 0.6321
1.250 0.1404 0.00677 0.00137 0.0021 0.3789 0.6451
1.500 0.1696 0.00697 0.00145 0.0019 0.3393 0.6560
1.750 0.1990 0.00716 0.00152 0.0016 0.3040 0.6658
2.000 0.2282 0.00735 0.00161 0.0014 0.2722 0.6755
2.500 0.2866 0.00768 0.00180 0.0011 0.2265 0.6957
2.750 0.3156 0.00781 0.00190 0.0010 0.2097 0.7053
3.000 0.3448 0.00796 0.00200 0.0008 0.1939 0.7141
3.250 0.3738 0.00809 0.00211 0.0007 0.1803 0.7228
3.500 0.4028 0.00824 0.00223 0.0006 0.1667 0.7313
3.750 0.4317 0.00838 0.00234 0.0005 0.1545 0.7403
4.000 0.4606 0.00851 0.00246 0.0003 0.1440 0.7478
4.250 0.4895 0.00865 0.00260 0.0002 0.1322 0.7560
4.500 0.5180 0.00889 0.00276 0.0001 0.1128 0.7646
4.750 0.5454 0.00960 0.00318 -0.0001 0.0514 0.7743
5.000 0.5738 0.00985 0.00346 -0.0001 0.0451 0.7857
5.250 0.6020 0.01004 0.00372 -0.0001 0.0425 0.8001
5.500 0.6297 0.01028 0.00404 0.0000 0.0399 0.8209
5.750 0.6561 0.01045 0.00439 0.0004 0.0383 0.8621
6.000 0.6816 0.01040 0.00460 0.0013 0.0376 1.0000
6.250 0.7102 0.01068 0.00490 0.0012 0.0367 1.0000
6.500 0.7385 0.01099 0.00522 0.0011 0.0358 1.0000
6.750 0.7667 0.01132 0.00557 0.0010 0.0349 1.0000
7.000 0.7946 0.01170 0.00595 0.0009 0.0339 1.0000
7.250 0.8219 0.01221 0.00649 0.0009 0.0328 1.0000
7.500 0.8482 0.01297 0.00730 0.0009 0.0319 1.0000
7.750 0.8758 0.01331 0.00767 0.0009 0.0316 1.0000
8.000 0.9031 0.01368 0.00807 0.0009 0.0312 1.0000
8.250 0.9303 0.01405 0.00847 0.0010 0.0305 1.0000
8.500 0.9571 0.01448 0.00893 0.0010 0.0299 1.0000
8.750 0.9836 0.01495 0.00943 0.0011 0.0293 1.0000
9.000 1.0098 0.01542 0.00993 0.0012 0.0287 1.0000
9.250 1.0359 0.01591 0.01043 0.0013 0.0280 1.0000
9.500 1.0607 0.01658 0.01112 0.0014 0.0273 1.0000
9.750 1.0805 0.01816 0.01278 0.0019 0.0264 1.0000
10.000 1.1067 0.01848 0.01314 0.0020 0.0261 1.0000
10.250 1.1325 0.01885 0.01356 0.0022 0.0257 1.0000
10.500 1.1576 0.01932 0.01407 0.0024 0.0252 1.0000
10.750 1.1819 0.01987 0.01468 0.0026 0.0247 1.0000
11.000 1.2057 0.02045 0.01530 0.0029 0.0241 1.0000
11.250 1.2295 0.02099 0.01587 0.0032 0.0236 1.0000
11.500 1.2531 0.02152 0.01642 0.0034 0.0231 1.0000
11.750 1.2750 0.02222 0.01715 0.0037 0.0226 1.0000
12.000 1.2867 0.02424 0.01926 0.0047 0.0217 1.0000
12.250 1.3093 0.02471 0.01980 0.0051 0.0215 1.0000
12.500 1.3305 0.02532 0.02048 0.0055 0.0212 1.0000
12.750 1.3502 0.02603 0.02127 0.0060 0.0208 1.0000
13.000 1.3690 0.02679 0.02210 0.0065 0.0203 1.0000
13.250 1.3870 0.02754 0.02292 0.0070 0.0199 1.0000
13.500 1.4037 0.02831 0.02374 0.0076 0.0195 1.0000
13.750 1.4155 0.02927 0.02474 0.0086 0.0191 1.0000
14.000 1.4257 0.03053 0.02606 0.0090 0.0188 1.0000
14.250 1.4332 0.03227 0.02787 0.0089 0.0185 1.0000
14.500 1.4347 0.03492 0.03061 0.0082 0.0182 1.0000
14.750 1.4224 0.03945 0.03528 0.0065 0.0178 1.0000
15.000 1.4275 0.04212 0.03806 0.0052 0.0177 1.0000
15.250 1.4304 0.04515 0.04119 0.0037 0.0175 1.0000
15.500 1.4297 0.04880 0.04496 0.0018 0.0173 1.0000
15.750 1.4252 0.05306 0.04934 -0.0005 0.0172 1.0000
16.000 1.4173 0.05798 0.05438 -0.0032 0.0170 1.0000
16.250 1.4064 0.06349 0.06002 -0.0063 0.0168 1.0000
16.500 1.3929 0.06948 0.06613 -0.0095 0.0167 1.0000
16.750 1.3760 0.07602 0.07278 -0.0130 0.0166 1.0000
17.000 1.3580 0.08277 0.07965 -0.0165 0.0165 1.0000
17.250 1.3396 0.08972 0.08671 -0.0201 0.0164 1.0000
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Polar data table (+)
Polar graphs
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