GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 50,000 Max Cl/Cd: 28.16 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe11k-il-50000.txt Download as CSV file: xf-goe11k-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 11K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4948 0.10681 0.09990 -0.0206 1.0000 0.2168
-8.000 -0.4829 0.10251 0.09561 -0.0186 1.0000 0.2279
-7.750 -0.5135 0.10232 0.09561 -0.0173 1.0000 0.2320
-7.500 -0.5014 0.09811 0.09141 -0.0151 1.0000 0.2447
-7.250 -0.5029 0.09507 0.08843 -0.0130 1.0000 0.2536
-7.000 -0.5313 0.09428 0.08781 -0.0118 1.0000 0.2616
-6.750 -0.5270 0.09089 0.08446 -0.0092 1.0000 0.2752
-6.500 -0.5288 0.08797 0.08159 -0.0069 1.0000 0.2895
-6.250 -0.5368 0.08551 0.07918 -0.0051 1.0000 0.3055
-6.000 -0.5287 0.08216 0.07587 -0.0009 1.0000 0.3291
-5.750 -0.5452 0.08046 0.07425 0.0007 1.0000 0.3510
-5.500 -0.5356 0.07713 0.07097 0.0063 1.0000 0.3842
-5.250 -0.5296 0.07443 0.06831 0.0115 1.0000 0.4199
-4.750 -0.2194 0.05653 0.04935 0.0017 1.0000 0.9024
-4.500 -0.2388 0.05550 0.04845 0.0067 1.0000 0.8819
-4.250 -0.2915 0.05605 0.04927 0.0172 1.0000 0.8406
-3.750 -0.4374 0.04450 0.03619 -0.0222 1.0000 0.2058
-3.500 -0.4106 0.04041 0.03141 -0.0226 1.0000 0.1809
-3.250 -0.3855 0.03757 0.02765 -0.0221 1.0000 0.1730
-3.000 -0.3650 0.03514 0.02505 -0.0211 1.0000 0.1776
-2.750 -0.3412 0.03298 0.02232 -0.0201 1.0000 0.1769
-2.500 -0.3188 0.03140 0.02039 -0.0189 1.0000 0.1839
-2.250 -0.2949 0.02991 0.01845 -0.0178 1.0000 0.1896
-2.000 -0.2709 0.02852 0.01690 -0.0169 1.0000 0.1951
-1.750 -0.2464 0.02748 0.01562 -0.0162 1.0000 0.2067
-1.500 -0.2205 0.02654 0.01445 -0.0155 1.0000 0.2155
-1.250 -0.1910 0.02566 0.01346 -0.0155 1.0000 0.2265
-1.000 -0.1618 0.02501 0.01271 -0.0155 1.0000 0.2475
-0.750 -0.1339 0.02427 0.01211 -0.0155 1.0000 0.2774
-0.500 -0.0598 0.02111 0.01112 -0.0233 1.0000 1.0000
-0.250 -0.0389 0.02133 0.01092 -0.0221 1.0000 1.0000
0.000 -0.0182 0.02157 0.01087 -0.0209 1.0000 1.0000
0.250 0.0023 0.02182 0.01088 -0.0199 1.0000 1.0000
0.500 0.0227 0.02210 0.01096 -0.0189 1.0000 1.0000
0.750 0.0432 0.02240 0.01110 -0.0179 1.0000 1.0000
1.000 0.0636 0.02271 0.01129 -0.0169 1.0000 1.0000
1.250 0.0839 0.02305 0.01152 -0.0160 1.0000 1.0000
1.500 0.1041 0.02341 0.01180 -0.0151 1.0000 1.0000
1.750 0.1243 0.02379 0.01212 -0.0142 1.0000 1.0000
2.000 0.1443 0.02419 0.01249 -0.0134 1.0000 1.0000
2.250 0.1643 0.02462 0.01291 -0.0126 1.0000 1.0000
2.500 0.1840 0.02508 0.01337 -0.0118 1.0000 1.0000
2.750 0.2036 0.02557 0.01388 -0.0110 1.0000 1.0000
3.000 0.2230 0.02609 0.01444 -0.0102 1.0000 1.0000
3.250 0.2421 0.02665 0.01506 -0.0095 1.0000 1.0000
3.500 0.2609 0.02726 0.01576 -0.0088 1.0000 1.0000
3.750 0.2792 0.02791 0.01651 -0.0081 1.0000 1.0000
4.000 0.2971 0.02863 0.01734 -0.0075 1.0000 1.0000
4.250 0.3142 0.02942 0.01827 -0.0069 1.0000 1.0000
4.500 0.3306 0.03032 0.01934 -0.0064 1.0000 1.0000
4.750 0.3458 0.03133 0.02053 -0.0059 1.0000 1.0000
5.000 0.3595 0.03253 0.02192 -0.0056 1.0000 1.0000
5.250 0.6442 0.02784 0.01919 -0.0414 0.8170 1.0000
5.500 0.7409 0.02631 0.01437 -0.0401 0.2391 1.0000
5.750 0.8119 0.02910 0.01692 -0.0475 0.1908 1.0000
6.000 0.8647 0.03199 0.01985 -0.0515 0.1660 1.0000
6.250 0.8982 0.03461 0.02267 -0.0520 0.1506 1.0000
6.500 0.9288 0.03769 0.02595 -0.0521 0.1410 1.0000
6.750 0.9489 0.04016 0.02885 -0.0501 0.1330 1.0000
7.000 0.9735 0.04381 0.03274 -0.0493 0.1297 1.0000
7.250 0.9863 0.04710 0.03654 -0.0463 0.1278 1.0000
7.500 0.9927 0.05008 0.04012 -0.0423 0.1262 1.0000
7.750 0.9988 0.05356 0.04407 -0.0387 0.1260 1.0000
8.000 1.0092 0.05800 0.04877 -0.0363 0.1282 1.0000
8.250 0.9950 0.06165 0.05328 -0.0303 0.1361 1.0000
8.500 1.0046 0.06707 0.05883 -0.0285 0.1423 1.0000
8.750 0.9850 0.07174 0.06407 -0.0239 0.1554 1.0000
9.000 0.9527 0.07708 0.06987 -0.0201 0.1754 1.0000
9.250 0.9198 0.08334 0.07632 -0.0183 0.1977 1.0000
9.500 0.8632 0.08968 0.08267 -0.0189 0.2198 1.0000
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