GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 55 AIRFOIL (goe55-il) Reynolds number: 100,000 Max Cl/Cd: 42.35 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe55-il-100000.txt Download as CSV file: xf-goe55-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 55 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6211 0.11228 0.10724 0.0386 1.0000 0.0842
-8.250 -0.6202 0.10922 0.10421 0.0354 1.0000 0.0872
-8.000 -0.6275 0.10713 0.10219 0.0249 1.0000 0.0889
-7.750 -0.6215 0.10214 0.09720 0.0160 1.0000 0.0898
-7.500 -0.6100 0.09728 0.09238 0.0247 1.0000 0.0913
-7.250 -0.5985 0.09359 0.08871 0.0261 1.0000 0.0935
-7.000 -0.5877 0.08987 0.08500 0.0239 1.0000 0.0964
-6.750 -0.5658 0.08555 0.08038 0.0012 1.0000 0.1031
-6.500 -0.5580 0.08008 0.07509 0.0062 1.0000 0.1046
-6.250 -0.5464 0.07682 0.07188 0.0097 1.0000 0.1073
-6.000 -0.5292 0.07314 0.06818 0.0072 1.0000 0.1121
-5.750 -0.5021 0.06761 0.06241 -0.0039 1.0000 0.1190
-5.500 -0.4877 0.06428 0.05916 -0.0020 1.0000 0.1217
-5.250 -0.4551 0.06011 0.05462 -0.0110 1.0000 0.1332
-5.000 -0.4408 0.05661 0.05128 -0.0087 1.0000 0.1362
-4.750 -0.4127 0.05309 0.04755 -0.0130 1.0000 0.1494
-4.500 -0.3930 0.05031 0.04485 -0.0123 1.0000 0.1562
-4.250 -0.3665 0.04704 0.04146 -0.0147 1.0000 0.1682
-4.000 -0.3328 0.04543 0.03947 -0.0186 1.0000 0.1931
-3.750 -0.3136 0.04149 0.03573 -0.0179 1.0000 0.1989
-3.500 -0.2721 0.02399 0.01866 -0.0182 1.0000 0.2269
-3.250 -0.2520 0.02183 0.01660 -0.0174 1.0000 0.2480
-3.000 -0.2303 0.01974 0.01454 -0.0171 1.0000 0.2802
-2.750 -0.1574 0.02671 0.01862 -0.0285 1.0000 0.1186
-2.500 -0.1272 0.02431 0.01611 -0.0288 1.0000 0.1117
-2.250 -0.0961 0.02249 0.01402 -0.0290 1.0000 0.1104
-2.000 -0.0654 0.02094 0.01224 -0.0291 1.0000 0.1100
-1.750 -0.0350 0.01953 0.01062 -0.0290 1.0000 0.1091
-1.500 -0.0053 0.01837 0.00935 -0.0288 1.0000 0.1103
-1.250 0.0240 0.01740 0.00834 -0.0286 1.0000 0.1137
-1.000 0.0530 0.01642 0.00741 -0.0284 1.0000 0.1201
-0.750 0.0818 0.01553 0.00672 -0.0282 1.0000 0.1271
-0.500 0.1113 0.01460 0.00610 -0.0283 1.0000 0.1366
-0.250 0.1452 0.01491 0.00573 -0.0276 0.6712 0.1602
0.000 0.1712 0.01472 0.00535 -0.0266 0.6013 0.2091
0.250 0.1922 0.01224 0.00482 -0.0240 0.5717 1.0000
0.500 0.2205 0.01264 0.00480 -0.0236 0.5487 1.0000
0.750 0.2487 0.01304 0.00490 -0.0234 0.5314 1.0000
1.000 0.2773 0.01343 0.00506 -0.0232 0.5174 1.0000
1.250 0.3058 0.01383 0.00528 -0.0231 0.5043 1.0000
1.500 0.3339 0.01422 0.00550 -0.0229 0.4889 1.0000
1.750 0.3620 0.01461 0.00573 -0.0227 0.4731 1.0000
2.000 0.3900 0.01502 0.00599 -0.0224 0.4591 1.0000
2.250 0.4180 0.01546 0.00631 -0.0222 0.4470 1.0000
2.500 0.4465 0.01584 0.00668 -0.0222 0.4347 1.0000
2.750 0.4748 0.01628 0.00710 -0.0221 0.4227 1.0000
3.000 0.5027 0.01675 0.00753 -0.0219 0.4106 1.0000
3.250 0.5305 0.01724 0.00795 -0.0216 0.3976 1.0000
3.500 0.5581 0.01767 0.00835 -0.0214 0.3819 1.0000
3.750 0.5856 0.01799 0.00871 -0.0211 0.3627 1.0000
4.000 0.6127 0.01824 0.00895 -0.0208 0.3425 1.0000
4.250 0.6398 0.01847 0.00913 -0.0204 0.3232 1.0000
4.500 0.6669 0.01869 0.00930 -0.0200 0.3048 1.0000
4.750 0.6943 0.01878 0.00951 -0.0197 0.2838 1.0000
5.000 0.7216 0.01859 0.00936 -0.0194 0.2608 1.0000
5.250 0.7492 0.01841 0.00928 -0.0191 0.2349 1.0000
5.500 0.7767 0.01834 0.00917 -0.0188 0.1998 1.0000
5.750 0.8021 0.01971 0.01007 -0.0187 0.1416 1.0000
6.000 0.8277 0.02129 0.01151 -0.0185 0.1162 1.0000
6.250 0.8537 0.02258 0.01279 -0.0181 0.1046 1.0000
6.500 0.8793 0.02408 0.01426 -0.0177 0.0983 1.0000
6.750 0.9057 0.02550 0.01583 -0.0172 0.0936 1.0000
7.000 0.9314 0.02702 0.01738 -0.0168 0.0901 1.0000
7.250 0.9564 0.02917 0.01951 -0.0165 0.0873 1.0000
7.500 0.9817 0.03094 0.02170 -0.0161 0.0846 1.0000
7.750 1.0058 0.03307 0.02419 -0.0157 0.0822 1.0000
8.000 1.0286 0.03570 0.02721 -0.0154 0.0810 1.0000
8.250 1.0493 0.03883 0.03079 -0.0152 0.0802 1.0000
8.500 1.0671 0.04247 0.03494 -0.0150 0.0795 1.0000
8.750 1.0841 0.04579 0.03858 -0.0149 0.0783 1.0000
9.000 1.1000 0.04914 0.04212 -0.0148 0.0769 1.0000
9.250 1.0819 0.05961 0.05382 -0.0177 0.0792 1.0000
9.500 1.0253 0.07659 0.07149 -0.0284 0.0841 1.0000
9.750 0.9890 0.09133 0.08628 -0.0408 0.0889 1.0000
10.000 0.9980 0.09324 0.08819 -0.0390 0.0881 1.0000
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Polar data table (+)
Polar graphs
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