GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 200,000 Max Cl/Cd: 72.89 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe11k-il-200000-n5.txt Download as CSV file: xf-goe11k-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4697 0.11913 0.11544 -0.0271 1.0000 0.0166
-10.250 -0.4703 0.11584 0.11218 -0.0271 1.0000 0.0158
-9.750 -0.4854 0.10600 0.10243 -0.0290 1.0000 0.0134
-9.500 -0.4889 0.10278 0.09926 -0.0287 1.0000 0.0133
-9.250 -0.4942 0.09950 0.09603 -0.0285 1.0000 0.0132
-9.000 -0.5002 0.09645 0.09302 -0.0280 1.0000 0.0132
-8.750 -0.5065 0.09380 0.09042 -0.0272 1.0000 0.0130
-8.500 -0.5121 0.09031 0.08696 -0.0279 0.9993 0.0129
-8.250 -0.5091 0.08517 0.08184 -0.0328 0.9960 0.0129
-8.000 -0.5099 0.07957 0.07627 -0.0384 0.9910 0.0129
-7.750 -0.4990 0.07269 0.06936 -0.0468 0.9868 0.0128
-7.500 -0.4933 0.06528 0.06188 -0.0536 0.9805 0.0128
-7.250 -0.4878 0.05521 0.05160 -0.0610 0.9750 0.0132
-7.000 -0.4833 0.04531 0.04135 -0.0651 0.9691 0.0130
-6.750 -0.4922 0.03094 0.02575 -0.0650 0.9629 0.0134
-6.500 -0.4785 0.02702 0.02121 -0.0639 0.9591 0.0138
-6.250 -0.4557 0.02501 0.01885 -0.0637 0.9567 0.0144
-6.000 -0.4306 0.02329 0.01679 -0.0638 0.9551 0.0153
-5.750 -0.4089 0.02187 0.01504 -0.0629 0.9525 0.0167
-5.500 -0.3899 0.02050 0.01333 -0.0613 0.9487 0.0183
-5.250 -0.3657 0.01949 0.01213 -0.0608 0.9460 0.0202
-5.000 -0.3388 0.01876 0.01123 -0.0607 0.9440 0.0228
-4.750 -0.3114 0.01785 0.01014 -0.0607 0.9425 0.0270
-4.500 -0.2812 0.01750 0.00973 -0.0613 0.9411 0.0331
-4.250 -0.2565 0.01726 0.00937 -0.0607 0.9382 0.0398
-4.000 -0.2339 0.01727 0.00917 -0.0596 0.9342 0.0478
-3.750 -0.2081 0.01695 0.00884 -0.0594 0.9317 0.0543
-3.500 -0.1798 0.01674 0.00845 -0.0596 0.9297 0.0609
-3.250 -0.1508 0.01641 0.00811 -0.0601 0.9280 0.0666
-3.000 -0.1206 0.01608 0.00768 -0.0607 0.9266 0.0716
-2.750 -0.0902 0.01567 0.00726 -0.0614 0.9254 0.0752
-2.500 -0.0749 0.01554 0.00708 -0.0589 0.9200 0.0771
-2.250 -0.0498 0.01531 0.00680 -0.0584 0.9172 0.0795
-2.000 -0.0219 0.01510 0.00652 -0.0585 0.9150 0.0815
-1.750 0.0071 0.01482 0.00625 -0.0588 0.9132 0.0843
-1.500 0.0374 0.01460 0.00603 -0.0595 0.9118 0.0898
-1.250 0.0683 0.01441 0.00583 -0.0602 0.9106 0.0958
-1.000 0.0837 0.01441 0.00588 -0.0577 0.9052 0.1050
-0.750 0.1085 0.01427 0.00583 -0.0572 0.9020 0.1268
-0.500 0.1358 0.01399 0.00576 -0.0573 0.8997 0.1850
-0.250 0.1629 0.01331 0.00568 -0.0575 0.8977 0.3606
0.250 0.3209 0.01197 0.00610 -0.0806 0.9039 1.0000
0.500 0.3504 0.01191 0.00600 -0.0809 0.9004 1.0000
0.750 0.3833 0.01180 0.00588 -0.0820 0.8981 1.0000
1.000 0.4211 0.01159 0.00567 -0.0840 0.8961 1.0000
1.250 0.4405 0.01160 0.00568 -0.0821 0.8880 1.0000
1.500 0.4866 0.01108 0.00518 -0.0854 0.8821 1.0000
1.750 0.5118 0.01093 0.00505 -0.0846 0.8724 1.0000
2.000 0.5566 0.01056 0.00473 -0.0879 0.8646 1.0000
2.250 0.5850 0.01033 0.00453 -0.0875 0.8483 1.0000
2.500 0.6224 0.00999 0.00420 -0.0890 0.8205 1.0000
2.750 0.6619 0.00975 0.00391 -0.0910 0.7769 1.0000
3.000 0.7085 0.00972 0.00362 -0.0945 0.6890 1.0000
3.250 0.7033 0.01100 0.00375 -0.0870 0.4744 1.0000
3.750 0.7147 0.01255 0.00452 -0.0779 0.3080 1.0000
4.000 0.7215 0.01352 0.00495 -0.0739 0.1992 1.0000
4.250 0.7350 0.01424 0.00540 -0.0713 0.1400 1.0000
4.500 0.7521 0.01476 0.00581 -0.0692 0.1140 1.0000
4.750 0.7700 0.01521 0.00624 -0.0672 0.1011 1.0000
5.000 0.7879 0.01567 0.00669 -0.0653 0.0894 1.0000
5.250 0.8057 0.01613 0.00713 -0.0634 0.0789 1.0000
5.500 0.8236 0.01658 0.00759 -0.0615 0.0705 1.0000
5.750 0.8417 0.01704 0.00806 -0.0597 0.0617 1.0000
6.000 0.8606 0.01746 0.00853 -0.0580 0.0509 1.0000
6.250 0.8800 0.01786 0.00898 -0.0564 0.0366 1.0000
6.500 0.8973 0.01853 0.00960 -0.0544 0.0278 1.0000
6.750 0.9143 0.01928 0.01038 -0.0524 0.0228 1.0000
7.000 0.9297 0.02030 0.01149 -0.0500 0.0197 1.0000
7.250 0.9469 0.02119 0.01252 -0.0481 0.0180 1.0000
7.500 0.9646 0.02204 0.01344 -0.0463 0.0161 1.0000
7.750 0.9814 0.02323 0.01471 -0.0445 0.0146 1.0000
8.000 1.0002 0.02447 0.01613 -0.0430 0.0138 1.0000
8.250 1.0194 0.02582 0.01767 -0.0416 0.0130 1.0000
8.500 1.0375 0.02714 0.01912 -0.0401 0.0122 1.0000
8.750 1.0537 0.02861 0.02068 -0.0385 0.0116 1.0000
9.000 1.0714 0.03034 0.02275 -0.0369 0.0105 1.0000
9.250 1.0868 0.03242 0.02514 -0.0350 0.0101 1.0000
9.500 1.0978 0.03456 0.02760 -0.0324 0.0098 1.0000
9.750 1.1047 0.03673 0.03007 -0.0292 0.0095 1.0000
10.000 1.1075 0.03900 0.03268 -0.0256 0.0093 1.0000
10.250 1.1068 0.04128 0.03524 -0.0215 0.0091 1.0000
10.500 1.1032 0.04361 0.03784 -0.0174 0.0090 1.0000
10.750 1.0979 0.04585 0.04028 -0.0135 0.0088 1.0000
11.000 1.0886 0.04846 0.04308 -0.0095 0.0087 1.0000
11.250 1.0725 0.05184 0.04680 -0.0053 0.0086 1.0000
11.750 1.0338 0.05959 0.05514 0.0009 0.0086 1.0000
12.000 1.0050 0.06546 0.06136 0.0024 0.0089 1.0000
12.250 0.9862 0.07017 0.06623 0.0022 0.0089 1.0000
12.500 0.9726 0.07449 0.07063 0.0009 0.0086 1.0000
12.750 0.9502 0.08179 0.07808 -0.0029 0.0087 1.0000
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Polar data table (+)
Polar graphs
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