GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 50,000 Max Cl/Cd: 16.12 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe655-il-50000.txt Download as CSV file: xf-goe655-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2939 0.12113 0.11437 -0.0300 1.0000 0.2448
-9.500 -0.2585 0.11467 0.10784 -0.0281 1.0000 0.2540
-9.250 -0.2855 0.11545 0.10880 -0.0276 1.0000 0.2609
-9.000 -0.2600 0.11009 0.10344 -0.0260 1.0000 0.2687
-8.750 -0.2789 0.10993 0.10342 -0.0248 1.0000 0.2771
-8.500 -0.2708 0.10626 0.09982 -0.0233 1.0000 0.2825
-8.250 -0.2718 0.10437 0.09801 -0.0214 1.0000 0.2912
-8.000 -0.3073 0.10496 0.09883 -0.0190 1.0000 0.2963
-7.750 -0.2806 0.10035 0.09419 -0.0172 1.0000 0.3047
-7.500 -0.3212 0.10167 0.09574 -0.0137 1.0000 0.3120
-7.250 -0.2993 0.09732 0.09140 -0.0119 1.0000 0.3204
-7.000 -0.3316 0.09781 0.09206 -0.0079 1.0000 0.3283
-6.750 -0.3260 0.09489 0.08921 -0.0055 1.0000 0.3363
-6.500 -0.3552 0.09506 0.08953 -0.0013 1.0000 0.3450
-6.250 -0.3652 0.09316 0.08774 0.0018 1.0000 0.3513
-6.000 -0.3847 0.09255 0.08724 0.0058 1.0000 0.3618
-5.500 -0.4245 0.09039 0.08530 0.0122 1.0000 0.3807
-5.250 -0.4177 0.08748 0.08244 0.0148 1.0000 0.3891
-5.000 -0.4407 0.08624 0.08131 0.0173 1.0000 0.4021
-4.750 -0.4596 0.08508 0.08024 0.0194 1.0000 0.4177
-4.500 -0.4436 0.05580 0.04924 -0.0281 1.0000 0.1764
-4.250 -0.4297 0.05241 0.04565 -0.0285 1.0000 0.1719
-4.000 -0.4130 0.04840 0.04114 -0.0300 1.0000 0.1681
-3.750 -0.3963 0.04578 0.03813 -0.0305 1.0000 0.1686
-3.500 -0.3446 0.04293 0.03463 -0.0366 0.9867 0.1703
-3.250 -0.2931 0.04078 0.03181 -0.0419 0.9721 0.1748
-3.000 -0.2441 0.03939 0.03006 -0.0464 0.9568 0.1836
-2.750 -0.1958 0.03823 0.02840 -0.0503 0.9411 0.1942
-2.500 -0.1509 0.03740 0.02747 -0.0535 0.9253 0.2119
-2.250 -0.1073 0.03665 0.02681 -0.0563 0.9094 0.2363
-2.000 -0.0665 0.03590 0.02618 -0.0583 0.8936 0.2815
-1.750 -0.0289 0.03501 0.02576 -0.0595 0.8782 0.3827
-1.500 0.0037 0.03428 0.02561 -0.0594 0.8627 0.5058
-1.250 0.0330 0.03361 0.02555 -0.0584 0.8474 0.6225
-1.000 0.1424 0.03227 0.02501 -0.0709 0.8324 1.0000
-0.750 0.1840 0.03247 0.02463 -0.0739 0.8155 1.0000
-0.500 0.2231 0.03269 0.02446 -0.0759 0.7992 1.0000
-0.250 0.2614 0.03288 0.02433 -0.0775 0.7832 1.0000
0.000 0.2995 0.03303 0.02421 -0.0788 0.7679 1.0000
0.250 0.3404 0.03307 0.02400 -0.0805 0.7537 1.0000
0.500 0.3990 0.03248 0.02316 -0.0842 0.7433 1.0000
0.750 0.4243 0.03289 0.02339 -0.0835 0.7278 1.0000
1.000 0.4465 0.03347 0.02382 -0.0825 0.7128 1.0000
1.250 0.4671 0.03419 0.02440 -0.0814 0.6987 1.0000
1.500 0.4964 0.03461 0.02468 -0.0813 0.6871 1.0000
1.750 0.5344 0.03460 0.02453 -0.0821 0.6770 1.0000
2.000 0.5406 0.03607 0.02592 -0.0796 0.6632 1.0000
2.250 0.5546 0.03729 0.02705 -0.0781 0.6519 1.0000
2.500 0.5897 0.03751 0.02717 -0.0786 0.6437 1.0000
2.750 0.5789 0.04016 0.02977 -0.0750 0.6315 1.0000
3.000 0.6335 0.03931 0.02882 -0.0771 0.6256 1.0000
3.250 0.6005 0.04330 0.03279 -0.0719 0.6131 1.0000
3.500 0.6249 0.04430 0.03374 -0.0717 0.6062 1.0000
3.750 0.5924 0.04872 0.03814 -0.0676 0.5964 1.0000
4.000 0.6058 0.05048 0.03986 -0.0667 0.5892 1.0000
4.250 0.5856 0.05447 0.04383 -0.0645 0.5811 1.0000
4.500 0.6258 0.05451 0.04382 -0.0648 0.5743 1.0000
4.750 0.5968 0.05902 0.04832 -0.0623 0.5650 1.0000
5.000 0.6195 0.06003 0.04930 -0.0617 0.5554 1.0000
5.250 0.6472 0.06052 0.04977 -0.0610 0.5448 1.0000
5.500 0.6304 0.06437 0.05360 -0.0594 0.5351 1.0000
5.750 0.6853 0.06294 0.05215 -0.0593 0.5252 1.0000
6.000 0.6519 0.06827 0.05749 -0.0578 0.5157 1.0000
6.250 0.6721 0.06962 0.05885 -0.0571 0.5062 1.0000
6.500 0.6842 0.07153 0.06078 -0.0563 0.4961 1.0000
6.750 0.6730 0.07547 0.06473 -0.0556 0.4865 1.0000
7.000 0.7346 0.07345 0.06273 -0.0548 0.4766 1.0000
7.250 0.6819 0.08109 0.07037 -0.0545 0.4671 1.0000
7.500 0.7013 0.08273 0.07204 -0.0539 0.4569 1.0000
7.750 0.6978 0.08638 0.07571 -0.0537 0.4479 1.0000
8.000 0.7038 0.08966 0.07901 -0.0536 0.4410 1.0000
8.250 0.6840 0.09540 0.08479 -0.0545 0.4388 1.0000
8.500 0.6744 0.10040 0.08982 -0.0554 0.4386 1.0000
8.750 0.6724 0.10508 0.09453 -0.0564 0.4406 1.0000
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Polar data table (+)
Polar graphs
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