GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 101 AIRFOIL (goe101-il) Reynolds number: 500,000 Max Cl/Cd: 104.4 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe101-il-500000.txt Download as CSV file: xf-goe101-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 101 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3790 0.09443 0.09222 -0.0190 1.0000 0.0153
-8.000 -0.3765 0.09153 0.08934 -0.0202 1.0000 0.0153
-7.750 -0.3763 0.08867 0.08652 -0.0212 1.0000 0.0153
-7.500 -0.3723 0.08546 0.08334 -0.0231 1.0000 0.0154
-7.250 -0.3656 0.08175 0.07965 -0.0262 1.0000 0.0154
-7.000 -0.3574 0.07821 0.07613 -0.0288 1.0000 0.0154
-6.750 -0.3592 0.07367 0.07162 -0.0275 1.0000 0.0158
-6.500 -0.3525 0.07101 0.06898 -0.0273 1.0000 0.0162
-6.250 -0.3448 0.06821 0.06619 -0.0283 1.0000 0.0166
-6.000 -0.3370 0.06538 0.06337 -0.0294 1.0000 0.0171
-5.750 -0.3295 0.06245 0.06044 -0.0305 1.0000 0.0178
-5.500 -0.2875 0.05711 0.05498 -0.0401 0.9959 0.0198
-5.250 -0.2337 0.05145 0.04909 -0.0507 0.9903 0.0208
-5.000 -0.1954 0.04621 0.04367 -0.0567 0.9852 0.0209
-4.750 -0.1591 0.04109 0.03832 -0.0615 0.9793 0.0209
-4.500 -0.1326 0.03454 0.03164 -0.0664 0.9724 0.0221
-4.250 -0.1011 0.03220 0.02921 -0.0690 0.9638 0.0234
-4.000 -0.0650 0.02938 0.02617 -0.0717 0.9542 0.0262
-3.750 -0.0253 0.02811 0.02447 -0.0724 0.9408 0.0287
-3.500 -0.0006 0.02196 0.01780 -0.0735 0.9225 0.0299
-3.250 0.0245 0.02031 0.01606 -0.0737 0.9014 0.0314
-3.000 0.0496 0.01912 0.01467 -0.0733 0.8776 0.0337
-2.750 0.0785 0.02028 0.01551 -0.0720 0.8510 0.0393
-2.500 0.1001 0.01639 0.01127 -0.0719 0.8252 0.0431
-2.250 0.1252 0.01569 0.01034 -0.0712 0.7969 0.0474
-2.000 0.1504 0.01477 0.00910 -0.0705 0.7700 0.0556
-1.250 0.2305 0.01133 0.00476 -0.0680 0.7016 0.0437
-1.000 0.2569 0.01072 0.00398 -0.0674 0.6806 0.0424
-0.750 0.2830 0.01028 0.00341 -0.0668 0.6594 0.0422
-0.500 0.3092 0.00993 0.00295 -0.0663 0.6386 0.0416
-0.250 0.3352 0.00960 0.00251 -0.0658 0.6182 0.0421
0.000 0.3614 0.00939 0.00220 -0.0654 0.5999 0.0430
0.250 0.3879 0.00924 0.00197 -0.0650 0.5828 0.0439
0.500 0.4145 0.00915 0.00181 -0.0647 0.5667 0.0447
0.750 0.4412 0.00911 0.00170 -0.0644 0.5521 0.0467
1.000 0.4680 0.00909 0.00160 -0.0641 0.5390 0.0482
1.250 0.4948 0.00911 0.00153 -0.0638 0.5268 0.0496
1.500 0.5217 0.00913 0.00149 -0.0635 0.5150 0.0535
1.750 0.5542 0.00701 0.00165 -0.0652 0.5040 1.0000
2.000 0.5809 0.00713 0.00167 -0.0648 0.4956 1.0000
2.250 0.6075 0.00727 0.00172 -0.0645 0.4873 1.0000
2.500 0.6343 0.00738 0.00179 -0.0643 0.4780 1.0000
2.750 0.6608 0.00751 0.00187 -0.0640 0.4690 1.0000
3.000 0.6875 0.00763 0.00195 -0.0637 0.4602 1.0000
3.250 0.7143 0.00776 0.00206 -0.0635 0.4533 1.0000
3.500 0.7410 0.00789 0.00217 -0.0632 0.4461 1.0000
3.750 0.7677 0.00801 0.00231 -0.0630 0.4397 1.0000
4.000 0.7944 0.00814 0.00243 -0.0627 0.4322 1.0000
4.250 0.8211 0.00827 0.00257 -0.0625 0.4244 1.0000
4.500 0.8474 0.00842 0.00271 -0.0622 0.4140 1.0000
5.000 0.9001 0.00869 0.00299 -0.0616 0.3836 1.0000
5.250 0.9260 0.00887 0.00314 -0.0613 0.3611 1.0000
5.500 0.9514 0.00913 0.00332 -0.0609 0.3300 1.0000
5.750 0.9733 0.00984 0.00368 -0.0602 0.2510 1.0000
6.000 0.9936 0.01083 0.00428 -0.0593 0.1811 1.0000
6.250 1.0133 0.01191 0.00493 -0.0584 0.1029 1.0000
6.500 1.0301 0.01340 0.00594 -0.0569 0.0280 1.0000
6.750 1.0523 0.01416 0.00676 -0.0560 0.0212 1.0000
7.000 1.0755 0.01472 0.00743 -0.0552 0.0192 1.0000
7.250 1.0974 0.01543 0.00823 -0.0543 0.0173 1.0000
7.500 1.1171 0.01640 0.00929 -0.0531 0.0159 1.0000
7.750 1.1310 0.01802 0.01108 -0.0511 0.0147 1.0000
8.000 1.1490 0.01907 0.01223 -0.0497 0.0143 1.0000
8.250 1.1673 0.02006 0.01331 -0.0483 0.0138 1.0000
8.500 1.1855 0.02103 0.01439 -0.0469 0.0130 1.0000
8.750 1.2028 0.02207 0.01551 -0.0455 0.0123 1.0000
9.000 1.2184 0.02335 0.01687 -0.0439 0.0118 1.0000
9.250 1.2335 0.02471 0.01833 -0.0423 0.0114 1.0000
9.500 1.2481 0.02619 0.01990 -0.0407 0.0111 1.0000
9.750 1.2620 0.02789 0.02168 -0.0390 0.0107 1.0000
10.000 1.2759 0.02989 0.02382 -0.0375 0.0105 1.0000
10.250 1.2898 0.03222 0.02631 -0.0360 0.0104 1.0000
10.500 1.3023 0.03476 0.02904 -0.0344 0.0104 1.0000
10.750 1.2374 0.03050 0.02577 -0.0254 0.0122 1.0000
11.000 1.2166 0.03976 0.03545 -0.0223 0.0142 1.0000
11.250 1.2064 0.04082 0.03667 -0.0196 0.0138 1.0000
11.500 1.1855 0.04710 0.04351 -0.0167 0.0184 1.0000
11.750 1.1659 0.05150 0.04809 -0.0161 0.0183 1.0000
12.000 1.1459 0.05644 0.05321 -0.0164 0.0181 1.0000
12.250 1.1212 0.06288 0.05983 -0.0178 0.0184 1.0000
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Polar data table (+)
Polar graphs
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