GOE 113 AIRFOIL (goe113-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 113 AIRFOIL (goe113-il) Reynolds number: 500,000 Max Cl/Cd: 77.97 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe113-il-500000-n5.txt Download as CSV file: xf-goe113-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 113 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4274 0.08881 0.08669 -0.0133 1.0000 0.0071
-7.250 -0.4224 0.08513 0.08304 -0.0160 1.0000 0.0071
-7.000 -0.4198 0.08122 0.07915 -0.0168 1.0000 0.0065
-6.750 -0.4135 0.07714 0.07508 -0.0201 1.0000 0.0056
-6.500 -0.4056 0.07240 0.07035 -0.0240 1.0000 0.0051
-6.250 -0.3958 0.06726 0.06520 -0.0281 1.0000 0.0048
-6.000 -0.3839 0.06334 0.06126 -0.0308 1.0000 0.0049
-5.750 -0.3654 0.05996 0.05783 -0.0339 0.9991 0.0055
-5.500 -0.3311 0.05419 0.05194 -0.0413 0.9957 0.0065
-5.250 -0.2990 0.04861 0.04622 -0.0472 0.9917 0.0062
-5.000 -0.2643 0.04286 0.04026 -0.0527 0.9881 0.0058
-4.750 -0.2303 0.03705 0.03419 -0.0568 0.9833 0.0055
-4.500 -0.1948 0.03108 0.02786 -0.0601 0.9792 0.0053
-4.250 -0.1623 0.02550 0.02184 -0.0617 0.9725 0.0054
-4.000 -0.1293 0.01977 0.01550 -0.0626 0.9657 0.0059
-3.750 -0.0972 0.01317 0.00793 -0.0628 0.9590 0.0071
-3.500 -0.0662 0.01163 0.00610 -0.0633 0.9489 0.0089
-3.250 -0.0352 0.01109 0.00544 -0.0639 0.9346 0.0104
-3.000 -0.0050 0.01039 0.00459 -0.0642 0.9148 0.0125
-2.750 0.0238 0.01080 0.00494 -0.0643 0.8854 0.0153
-2.500 0.0504 0.01057 0.00448 -0.0636 0.8492 0.0199
-2.250 0.0764 0.01092 0.00458 -0.0630 0.8097 0.0227
-2.000 0.1019 0.01047 0.00390 -0.0625 0.7743 0.0249
-1.500 0.1547 0.01016 0.00331 -0.0619 0.7186 0.0294
-1.250 0.1813 0.01002 0.00299 -0.0617 0.6899 0.0306
-1.000 0.2081 0.00980 0.00261 -0.0614 0.6639 0.0305
-0.750 0.2350 0.00962 0.00228 -0.0612 0.6383 0.0302
-0.500 0.2622 0.00947 0.00200 -0.0611 0.6165 0.0298
-0.250 0.2896 0.00935 0.00177 -0.0611 0.5982 0.0296
0.000 0.3171 0.00925 0.00158 -0.0610 0.5821 0.0295
0.250 0.3447 0.00919 0.00143 -0.0610 0.5667 0.0295
0.500 0.3723 0.00916 0.00131 -0.0610 0.5508 0.0297
0.750 0.3999 0.00915 0.00122 -0.0610 0.5364 0.0302
1.000 0.4275 0.00917 0.00116 -0.0609 0.5194 0.0314
1.250 0.4549 0.00922 0.00113 -0.0609 0.5020 0.0334
1.500 0.4824 0.00889 0.00117 -0.0611 0.4849 0.2220
2.000 0.5315 0.00721 0.00133 -0.0601 0.4467 1.0000
2.500 0.5857 0.00756 0.00150 -0.0600 0.3997 1.0000
2.750 0.6121 0.00785 0.00161 -0.0599 0.3603 1.0000
3.000 0.6373 0.00837 0.00182 -0.0597 0.2896 1.0000
3.250 0.6625 0.00890 0.00209 -0.0595 0.2366 1.0000
3.500 0.6883 0.00931 0.00233 -0.0593 0.2003 1.0000
3.750 0.7147 0.00960 0.00253 -0.0592 0.1779 1.0000
4.000 0.7400 0.01009 0.00278 -0.0590 0.1321 1.0000
4.250 0.7654 0.01057 0.00311 -0.0588 0.1004 1.0000
4.500 0.7881 0.01154 0.00371 -0.0583 0.0184 1.0000
4.750 0.8142 0.01190 0.00414 -0.0580 0.0114 1.0000
5.000 0.8403 0.01224 0.00458 -0.0577 0.0098 1.0000
5.250 0.8659 0.01268 0.00514 -0.0573 0.0079 1.0000
5.500 0.8902 0.01336 0.00595 -0.0568 0.0066 1.0000
5.750 0.9149 0.01394 0.00663 -0.0563 0.0059 1.0000
6.000 0.9387 0.01467 0.00745 -0.0556 0.0054 1.0000
6.250 0.9616 0.01551 0.00839 -0.0549 0.0050 1.0000
6.500 0.9845 0.01626 0.00922 -0.0543 0.0045 1.0000
6.750 1.0058 0.01728 0.01033 -0.0534 0.0039 1.0000
7.000 1.0267 0.01837 0.01155 -0.0523 0.0036 1.0000
7.250 1.0466 0.01965 0.01295 -0.0510 0.0033 1.0000
7.500 1.0660 0.02106 0.01448 -0.0497 0.0031 1.0000
7.750 1.0853 0.02262 0.01617 -0.0483 0.0029 1.0000
8.000 1.1043 0.02437 0.01806 -0.0470 0.0028 1.0000
8.250 1.1228 0.02637 0.02025 -0.0456 0.0028 1.0000
8.500 1.1404 0.02870 0.02282 -0.0440 0.0028 1.0000
8.750 1.1561 0.03141 0.02586 -0.0422 0.0028 1.0000
9.000 1.1689 0.03448 0.02927 -0.0401 0.0029 1.0000
9.250 1.1783 0.03777 0.03290 -0.0378 0.0031 1.0000
9.500 1.1843 0.04095 0.03640 -0.0354 0.0031 1.0000
9.750 1.1879 0.04376 0.03948 -0.0331 0.0030 1.0000
10.000 1.1904 0.04600 0.04191 -0.0311 0.0028 1.0000
10.250 1.1886 0.04822 0.04430 -0.0287 0.0027 1.0000
10.500 1.1807 0.05045 0.04667 -0.0258 0.0026 1.0000
10.750 1.1692 0.05327 0.04965 -0.0236 0.0025 1.0000
11.000 1.1550 0.05683 0.05339 -0.0227 0.0025 1.0000
11.250 1.1405 0.06117 0.05792 -0.0232 0.0025 1.0000
11.500 1.1244 0.06625 0.06317 -0.0252 0.0025 1.0000
11.750 1.1096 0.07200 0.06909 -0.0283 0.0025 1.0000
12.000 1.0946 0.07848 0.07573 -0.0322 0.0025 1.0000
12.250 1.0786 0.08576 0.08317 -0.0369 0.0025 1.0000
12.500 1.0578 0.09514 0.09274 -0.0431 0.0026 1.0000
12.750 1.0242 0.10982 0.10765 -0.0526 0.0028 1.0000
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Polar data table (+)
Polar graphs
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