GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 178 AIRFOIL (goe178-il) Reynolds number: 500,000 Max Cl/Cd: 98.49 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe178-il-500000-n5.txt Download as CSV file: xf-goe178-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 178 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4131 0.10080 0.09862 -0.0107 1.0000 0.0094
-9.000 -0.4141 0.09549 0.09333 -0.0133 1.0000 0.0098
-8.750 -0.4164 0.09006 0.08792 -0.0163 1.0000 0.0103
-8.500 -0.4083 0.08753 0.08541 -0.0179 1.0000 0.0105
-8.250 -0.4005 0.08501 0.08291 -0.0196 1.0000 0.0108
-8.000 -0.3946 0.08221 0.08014 -0.0213 1.0000 0.0112
-7.750 -0.3854 0.07819 0.07613 -0.0256 0.9898 0.0117
-7.250 -0.3542 0.05704 0.05488 -0.0549 0.9602 0.0141
-7.000 -0.3300 0.02242 0.01870 -0.0873 0.9477 0.0187
-6.750 -0.3049 0.02073 0.01678 -0.0879 0.9361 0.0194
-6.500 -0.2792 0.02037 0.01638 -0.0878 0.9217 0.0199
-6.250 -0.2538 0.02007 0.01598 -0.0874 0.9011 0.0206
-6.000 -0.2295 0.01944 0.01516 -0.0869 0.8717 0.0215
-5.750 -0.2049 0.01836 0.01374 -0.0865 0.8414 0.0224
-5.500 -0.1792 0.01741 0.01244 -0.0863 0.8152 0.0234
-5.250 -0.1525 0.01667 0.01139 -0.0862 0.7916 0.0244
-5.000 -0.1253 0.01598 0.01040 -0.0861 0.7685 0.0249
-4.750 -0.0978 0.01551 0.00967 -0.0861 0.7437 0.0254
-4.500 -0.0705 0.01459 0.00842 -0.0862 0.7157 0.0261
-4.250 -0.0432 0.01351 0.00702 -0.0863 0.6834 0.0268
-4.000 -0.0157 0.01294 0.00619 -0.0863 0.6489 0.0272
-3.750 0.0120 0.01251 0.00552 -0.0863 0.6170 0.0276
-3.500 0.0398 0.01216 0.00497 -0.0863 0.5893 0.0280
-3.250 0.0678 0.01186 0.00448 -0.0863 0.5648 0.0283
-3.000 0.0959 0.01160 0.00408 -0.0864 0.5435 0.0289
-2.750 0.1241 0.01137 0.00372 -0.0865 0.5256 0.0295
-2.500 0.1524 0.01114 0.00337 -0.0865 0.5113 0.0298
-2.250 0.1808 0.01092 0.00306 -0.0866 0.4999 0.0301
-2.000 0.2093 0.01075 0.00279 -0.0867 0.4901 0.0306
-1.750 0.2378 0.01059 0.00256 -0.0868 0.4815 0.0311
-1.500 0.2663 0.01048 0.00237 -0.0868 0.4743 0.0318
-1.250 0.2948 0.01037 0.00221 -0.0869 0.4673 0.0325
-1.000 0.3232 0.01032 0.00208 -0.0870 0.4604 0.0332
-0.750 0.3517 0.01026 0.00197 -0.0870 0.4534 0.0338
-0.500 0.3801 0.01025 0.00188 -0.0871 0.4468 0.0343
-0.250 0.4086 0.01022 0.00182 -0.0872 0.4417 0.0351
0.000 0.4370 0.01019 0.00177 -0.0872 0.4369 0.0366
0.250 0.4654 0.01019 0.00174 -0.0873 0.4319 0.0405
0.500 0.4938 0.01011 0.00176 -0.0874 0.4269 0.0640
0.750 0.5222 0.01012 0.00178 -0.0874 0.4218 0.0754
1.000 0.5504 0.01017 0.00181 -0.0875 0.4173 0.0819
1.250 0.5786 0.01018 0.00184 -0.0876 0.4130 0.0894
1.500 0.6070 0.01018 0.00188 -0.0876 0.4091 0.1002
1.750 0.6352 0.01020 0.00193 -0.0877 0.4048 0.1139
2.000 0.6634 0.01012 0.00203 -0.0879 0.3992 0.1912
2.250 0.6919 0.00980 0.00215 -0.0883 0.3930 0.3718
3.250 0.7977 0.00884 0.00252 -0.0871 0.3695 1.0000
3.500 0.8258 0.00893 0.00262 -0.0872 0.3636 1.0000
3.750 0.8536 0.00907 0.00273 -0.0872 0.3568 1.0000
4.000 0.8815 0.00919 0.00284 -0.0872 0.3489 1.0000
4.250 0.9092 0.00934 0.00296 -0.0872 0.3386 1.0000
4.500 0.9366 0.00951 0.00310 -0.0872 0.3237 1.0000
4.750 0.9624 0.00995 0.00329 -0.0870 0.2780 1.0000
5.000 0.9871 0.01057 0.00366 -0.0868 0.2341 1.0000
5.250 1.0127 0.01104 0.00401 -0.0866 0.2101 1.0000
5.500 1.0379 0.01155 0.00437 -0.0864 0.1801 1.0000
5.750 1.0562 0.01322 0.00542 -0.0855 0.0620 1.0000
6.000 1.0818 0.01362 0.00580 -0.0852 0.0527 1.0000
6.250 1.1072 0.01402 0.00622 -0.0850 0.0441 1.0000
6.500 1.1323 0.01446 0.00663 -0.0847 0.0266 1.0000
6.750 1.1558 0.01513 0.00721 -0.0842 0.0159 1.0000
7.000 1.1803 0.01562 0.00776 -0.0837 0.0130 1.0000
7.250 1.2048 0.01608 0.00830 -0.0833 0.0121 1.0000
7.500 1.2286 0.01660 0.00890 -0.0828 0.0111 1.0000
7.750 1.2517 0.01719 0.00957 -0.0822 0.0102 1.0000
8.000 1.2732 0.01796 0.01041 -0.0814 0.0093 1.0000
8.250 1.2941 0.01874 0.01128 -0.0805 0.0086 1.0000
8.500 1.3157 0.01939 0.01202 -0.0798 0.0081 1.0000
8.750 1.3358 0.02015 0.01287 -0.0788 0.0077 1.0000
9.000 1.3548 0.02099 0.01379 -0.0778 0.0073 1.0000
9.250 1.3726 0.02188 0.01476 -0.0766 0.0069 1.0000
9.500 1.3889 0.02283 0.01579 -0.0752 0.0066 1.0000
9.750 1.4028 0.02393 0.01696 -0.0735 0.0064 1.0000
10.000 1.4111 0.02537 0.01849 -0.0713 0.0061 1.0000
10.250 1.4147 0.02685 0.02008 -0.0683 0.0059 1.0000
10.500 1.4221 0.02800 0.02136 -0.0659 0.0058 1.0000
10.750 1.4279 0.02937 0.02283 -0.0637 0.0056 1.0000
11.000 1.4326 0.03096 0.02453 -0.0618 0.0054 1.0000
11.250 1.4356 0.03284 0.02653 -0.0601 0.0052 1.0000
11.500 1.4372 0.03508 0.02889 -0.0589 0.0051 1.0000
11.750 1.4380 0.03762 0.03155 -0.0582 0.0049 1.0000
12.000 1.4383 0.04040 0.03445 -0.0577 0.0048 1.0000
12.250 1.4386 0.04335 0.03751 -0.0576 0.0047 1.0000
12.500 1.4381 0.04650 0.04078 -0.0577 0.0046 1.0000
12.750 1.4369 0.04984 0.04423 -0.0579 0.0046 1.0000
13.000 1.4358 0.05325 0.04774 -0.0583 0.0045 1.0000
13.250 1.4337 0.05680 0.05142 -0.0588 0.0044 1.0000
13.500 1.4308 0.06048 0.05521 -0.0593 0.0044 1.0000
13.750 1.4276 0.06422 0.05904 -0.0599 0.0043 1.0000
14.000 1.4233 0.06809 0.06302 -0.0605 0.0043 1.0000
14.250 1.4185 0.07207 0.06710 -0.0611 0.0042 1.0000
14.500 1.4130 0.07617 0.07130 -0.0618 0.0041 1.0000
14.750 1.4068 0.08042 0.07566 -0.0625 0.0041 1.0000
15.000 1.3992 0.08490 0.08027 -0.0633 0.0040 1.0000
15.250 1.3909 0.08955 0.08503 -0.0640 0.0040 1.0000
15.500 1.3848 0.09418 0.08981 -0.0653 0.0040 1.0000
15.750 1.3778 0.09901 0.09479 -0.0667 0.0039 1.0000
16.000 1.3701 0.10411 0.10004 -0.0684 0.0039 1.0000
16.250 1.3614 0.10946 0.10555 -0.0702 0.0039 1.0000
16.500 1.3522 0.11505 0.11128 -0.0724 0.0038 1.0000
16.750 1.3422 0.12094 0.11733 -0.0748 0.0038 1.0000
17.000 1.3314 0.12718 0.12374 -0.0776 0.0038 1.0000
17.250 1.3201 0.13368 0.13039 -0.0807 0.0038 1.0000
17.500 1.3080 0.14062 0.13750 -0.0842 0.0038 1.0000
17.750 1.2960 0.14781 0.14483 -0.0881 0.0038 1.0000
18.000 1.2837 0.15539 0.15256 -0.0924 0.0038 1.0000
18.250 1.2706 0.16352 0.16085 -0.0973 0.0038 1.0000
18.500 1.2571 0.17207 0.16954 -0.1025 0.0038 1.0000
18.750 1.2432 0.18118 0.17880 -0.1082 0.0038 1.0000
19.000 1.2280 0.19136 0.18911 -0.1147 0.0038 1.0000
19.250 1.2106 0.20334 0.20122 -0.1222 0.0039 1.0000
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