GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 598 AIRFOIL (goe598-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.84 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe598-il-1000000-n5.txt Download as CSV file: xf-goe598-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 598 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6584 0.08946 0.08798 0.0085 1.0000 0.0018
-8.750 -0.6635 0.08356 0.08210 0.0045 1.0000 0.0018
-7.750 -0.7246 0.02034 0.01678 -0.0272 1.0000 0.0019
-7.500 -0.7035 0.01791 0.01392 -0.0266 1.0000 0.0020
-7.250 -0.6804 0.01630 0.01202 -0.0262 1.0000 0.0021
-7.000 -0.6561 0.01512 0.01062 -0.0258 1.0000 0.0022
-6.750 -0.6318 0.01395 0.00924 -0.0254 1.0000 0.0022
-6.500 -0.6079 0.01265 0.00773 -0.0250 1.0000 0.0025
-6.250 -0.5823 0.01215 0.00717 -0.0248 1.0000 0.0027
-6.000 -0.5568 0.01164 0.00659 -0.0245 1.0000 0.0030
-5.750 -0.5316 0.01098 0.00582 -0.0241 1.0000 0.0033
-5.500 -0.5064 0.01038 0.00512 -0.0236 1.0000 0.0036
-5.250 -0.4812 0.00993 0.00456 -0.0232 1.0000 0.0038
-5.000 -0.4509 0.00929 0.00382 -0.0239 0.9975 0.0045
-4.750 -0.4195 0.00891 0.00340 -0.0248 0.9945 0.0053
-4.500 -0.3887 0.00860 0.00304 -0.0256 0.9903 0.0062
-4.250 -0.3573 0.00822 0.00265 -0.0265 0.9859 0.0088
-4.000 -0.3264 0.00795 0.00236 -0.0273 0.9797 0.0129
-3.750 -0.2958 0.00776 0.00219 -0.0280 0.9722 0.0191
-3.500 -0.2660 0.00756 0.00197 -0.0285 0.9633 0.0236
-3.250 -0.2376 0.00742 0.00180 -0.0286 0.9522 0.0277
-3.000 -0.2103 0.00733 0.00165 -0.0284 0.9384 0.0296
-2.750 -0.1838 0.00721 0.00148 -0.0281 0.9203 0.0318
-2.500 -0.1578 0.00713 0.00131 -0.0276 0.8969 0.0335
-2.250 -0.1318 0.00709 0.00115 -0.0271 0.8698 0.0352
-2.000 -0.1054 0.00707 0.00103 -0.0267 0.8420 0.0371
-1.750 -0.0785 0.00702 0.00092 -0.0265 0.8177 0.0470
-1.500 -0.0513 0.00695 0.00086 -0.0264 0.7968 0.0728
-1.250 -0.0237 0.00695 0.00079 -0.0264 0.7781 0.0763
-1.000 0.0039 0.00693 0.00074 -0.0263 0.7607 0.0822
-0.750 0.0316 0.00692 0.00069 -0.0263 0.7426 0.0866
-0.500 0.0591 0.00696 0.00065 -0.0263 0.7158 0.0911
-0.250 0.0866 0.00697 0.00061 -0.0263 0.6867 0.1032
0.000 0.1138 0.00671 0.00057 -0.0264 0.6646 0.2045
0.250 0.1413 0.00658 0.00056 -0.0265 0.6429 0.2646
0.500 0.1683 0.00618 0.00054 -0.0267 0.6239 0.4095
0.750 0.1953 0.00597 0.00057 -0.0267 0.5989 0.5123
1.000 0.2223 0.00577 0.00062 -0.0268 0.5732 0.6092
1.250 0.2480 0.00545 0.00068 -0.0265 0.5420 0.7462
1.500 0.2709 0.00547 0.00078 -0.0255 0.4515 0.8565
1.750 0.2914 0.00573 0.00094 -0.0238 0.3548 0.9466
2.000 0.3247 0.00614 0.00109 -0.0253 0.2740 0.9867
2.250 0.3550 0.00675 0.00127 -0.0263 0.1592 1.0000
2.500 0.3817 0.00707 0.00143 -0.0263 0.1146 1.0000
2.750 0.4078 0.00754 0.00164 -0.0262 0.0491 1.0000
3.000 0.4344 0.00790 0.00187 -0.0261 0.0167 1.0000
3.250 0.4616 0.00812 0.00209 -0.0260 0.0108 1.0000
3.500 0.4887 0.00841 0.00244 -0.0258 0.0078 1.0000
3.750 0.5158 0.00863 0.00267 -0.0257 0.0065 1.0000
4.000 0.5427 0.00892 0.00298 -0.0256 0.0055 1.0000
4.250 0.5690 0.00941 0.00354 -0.0253 0.0046 1.0000
4.500 0.5956 0.00980 0.00399 -0.0251 0.0042 1.0000
4.750 0.6217 0.01032 0.00459 -0.0248 0.0038 1.0000
5.000 0.6478 0.01076 0.00508 -0.0246 0.0034 1.0000
5.250 0.6740 0.01114 0.00548 -0.0244 0.0031 1.0000
5.500 0.6982 0.01210 0.00655 -0.0239 0.0027 1.0000
5.750 0.7236 0.01276 0.00730 -0.0235 0.0026 1.0000
6.000 0.7484 0.01357 0.00823 -0.0230 0.0025 1.0000
6.250 0.7726 0.01464 0.00946 -0.0224 0.0023 1.0000
6.500 0.7964 0.01597 0.01101 -0.0216 0.0020 1.0000
6.750 0.8191 0.01772 0.01302 -0.0207 0.0018 1.0000
7.000 0.8402 0.02021 0.01586 -0.0196 0.0017 1.0000
7.250 0.8521 0.02677 0.02316 -0.0167 0.0017 1.0000
7.500 0.8517 0.03772 0.03494 -0.0126 0.0019 1.0000
7.750 0.8558 0.04476 0.04238 -0.0108 0.0020 1.0000
8.000 0.8581 0.05126 0.04917 -0.0098 0.0021 1.0000
8.250 0.8578 0.05741 0.05555 -0.0096 0.0021 1.0000
8.500 0.8538 0.06344 0.06175 -0.0102 0.0022 1.0000
8.750 0.8460 0.06953 0.06798 -0.0120 0.0022 1.0000
9.000 0.8311 0.07538 0.07392 -0.0147 0.0023 1.0000
9.250 0.8172 0.08457 0.08316 -0.0252 0.0023 1.0000
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Polar data table (+)
Polar graphs
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