K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: K3311 (smoothed) (k3311sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.89 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3311sm-il-1000000.txt Download as CSV file: xf-k3311sm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: K3311 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4785 0.02502 0.02203 -0.0845 0.9736 0.0099
-8.000 -0.4566 0.02030 0.01670 -0.0863 0.9685 0.0101
-7.750 -0.4362 0.01647 0.01230 -0.0867 0.9601 0.0106
-7.500 -0.4067 0.01526 0.01094 -0.0877 0.9535 0.0110
-7.250 -0.3774 0.01452 0.01009 -0.0884 0.9449 0.0113
-7.000 -0.3496 0.01390 0.00936 -0.0886 0.9347 0.0117
-6.750 -0.3226 0.01324 0.00857 -0.0886 0.9236 0.0121
-6.500 -0.2969 0.01258 0.00777 -0.0882 0.9114 0.0125
-6.250 -0.2720 0.01199 0.00704 -0.0877 0.8987 0.0130
-6.000 -0.2469 0.01158 0.00652 -0.0871 0.8855 0.0135
-5.750 -0.2224 0.01109 0.00590 -0.0864 0.8723 0.0139
-5.500 -0.1999 0.01029 0.00499 -0.0855 0.8592 0.0152
-5.250 -0.1740 0.01013 0.00477 -0.0850 0.8463 0.0162
-5.000 -0.1485 0.00989 0.00446 -0.0845 0.8336 0.0173
-4.750 -0.1228 0.00969 0.00416 -0.0840 0.8206 0.0181
-4.500 -0.0994 0.00912 0.00347 -0.0831 0.8077 0.0198
-4.250 -0.0738 0.00893 0.00322 -0.0826 0.7950 0.0212
-4.000 -0.0478 0.00878 0.00301 -0.0821 0.7823 0.0228
-3.750 -0.0214 0.00868 0.00285 -0.0818 0.7700 0.0240
-3.500 0.0037 0.00834 0.00243 -0.0812 0.7580 0.0269
-3.250 0.0299 0.00821 0.00225 -0.0808 0.7466 0.0293
-3.000 0.0564 0.00814 0.00212 -0.0804 0.7351 0.0315
-2.750 0.0822 0.00791 0.00184 -0.0799 0.7238 0.0372
-2.500 0.1089 0.00783 0.00170 -0.0796 0.7130 0.0417
-2.250 0.1351 0.00766 0.00153 -0.0792 0.7027 0.0550
-2.000 0.1606 0.00744 0.00140 -0.0788 0.6926 0.0933
-1.750 0.1846 0.00694 0.00127 -0.0782 0.6827 0.2158
-1.500 0.2089 0.00655 0.00119 -0.0777 0.6734 0.3288
-1.250 0.2334 0.00627 0.00115 -0.0771 0.6638 0.4256
-1.000 0.2589 0.00607 0.00115 -0.0767 0.6545 0.5029
-0.750 0.2849 0.00599 0.00114 -0.0763 0.6455 0.5512
-0.500 0.3111 0.00594 0.00114 -0.0759 0.6360 0.5867
-0.250 0.3369 0.00584 0.00115 -0.0754 0.6270 0.6331
0.000 0.3616 0.00575 0.00118 -0.0747 0.6180 0.6897
0.250 0.3861 0.00562 0.00120 -0.0739 0.6091 0.7492
0.500 0.4107 0.00554 0.00123 -0.0731 0.6004 0.7961
0.750 0.4347 0.00545 0.00126 -0.0721 0.5914 0.8493
1.000 0.4696 0.00531 0.00131 -0.0735 0.5822 0.9301
1.250 0.5369 0.00538 0.00134 -0.0824 0.5713 0.9752
1.500 0.5751 0.00549 0.00139 -0.0847 0.5615 0.9957
1.750 0.6101 0.00557 0.00142 -0.0864 0.5515 1.0000
2.000 0.6348 0.00566 0.00146 -0.0857 0.5424 1.0000
2.250 0.6596 0.00576 0.00151 -0.0850 0.5329 1.0000
2.500 0.6848 0.00584 0.00156 -0.0845 0.5238 1.0000
2.750 0.7097 0.00594 0.00162 -0.0839 0.5147 1.0000
3.000 0.7347 0.00605 0.00169 -0.0833 0.5047 1.0000
3.250 0.7599 0.00615 0.00177 -0.0827 0.4954 1.0000
3.500 0.7848 0.00627 0.00185 -0.0821 0.4854 1.0000
3.750 0.8098 0.00639 0.00193 -0.0815 0.4748 1.0000
4.000 0.8348 0.00651 0.00203 -0.0810 0.4636 1.0000
4.250 0.8597 0.00665 0.00214 -0.0804 0.4520 1.0000
4.500 0.8844 0.00679 0.00225 -0.0797 0.4406 1.0000
4.750 0.9089 0.00695 0.00237 -0.0791 0.4287 1.0000
5.500 0.9817 0.00750 0.00281 -0.0771 0.3852 1.0000
5.750 1.0044 0.00778 0.00299 -0.0762 0.3597 1.0000
6.000 1.0262 0.00814 0.00322 -0.0751 0.3300 1.0000
6.250 1.0484 0.00847 0.00345 -0.0742 0.3045 1.0000
6.500 1.0694 0.00888 0.00373 -0.0730 0.2746 1.0000
6.750 1.0908 0.00927 0.00401 -0.0720 0.2491 1.0000
7.000 1.1116 0.00969 0.00433 -0.0708 0.2235 1.0000
7.250 1.1311 0.01021 0.00469 -0.0694 0.1928 1.0000
7.500 1.1499 0.01076 0.00508 -0.0680 0.1633 1.0000
7.750 1.1679 0.01135 0.00552 -0.0664 0.1343 1.0000
8.000 1.1850 0.01198 0.00600 -0.0647 0.1062 1.0000
8.250 1.2010 0.01266 0.00653 -0.0629 0.0788 1.0000
8.500 1.2159 0.01339 0.00712 -0.0608 0.0541 1.0000
8.750 1.2303 0.01412 0.00773 -0.0587 0.0359 1.0000
9.000 1.2458 0.01475 0.00831 -0.0567 0.0263 1.0000
9.250 1.2611 0.01534 0.00889 -0.0547 0.0213 1.0000
9.500 1.2761 0.01583 0.00941 -0.0526 0.0189 1.0000
9.750 1.2855 0.01654 0.01015 -0.0495 0.0162 1.0000
10.000 1.3002 0.01701 0.01067 -0.0474 0.0153 1.0000
10.250 1.3145 0.01752 0.01121 -0.0454 0.0142 1.0000
10.500 1.3271 0.01814 0.01186 -0.0432 0.0134 1.0000
10.750 1.3345 0.01907 0.01286 -0.0403 0.0122 1.0000
11.000 1.3443 0.01991 0.01377 -0.0380 0.0116 1.0000
11.250 1.3571 0.02060 0.01453 -0.0362 0.0111 1.0000
11.500 1.3682 0.02143 0.01541 -0.0343 0.0106 1.0000
11.750 1.3795 0.02228 0.01631 -0.0326 0.0101 1.0000
12.000 1.3885 0.02332 0.01742 -0.0308 0.0097 1.0000
12.250 1.3956 0.02457 0.01871 -0.0290 0.0092 1.0000
12.500 1.3909 0.02679 0.02107 -0.0264 0.0086 1.0000
12.750 1.3993 0.02812 0.02246 -0.0252 0.0084 1.0000
13.000 1.4057 0.02968 0.02411 -0.0239 0.0083 1.0000
13.250 1.4155 0.03100 0.02550 -0.0231 0.0079 1.0000
13.500 1.4211 0.03277 0.02736 -0.0221 0.0077 1.0000
13.750 1.4261 0.03465 0.02931 -0.0214 0.0074 1.0000
14.000 1.4266 0.03704 0.03181 -0.0206 0.0073 1.0000
14.250 1.4289 0.03933 0.03419 -0.0200 0.0071 1.0000
14.500 1.4328 0.04152 0.03644 -0.0197 0.0068 1.0000
14.750 1.4310 0.04437 0.03937 -0.0194 0.0066 1.0000
15.000 1.4272 0.04754 0.04265 -0.0193 0.0066 1.0000
15.250 1.4187 0.05138 0.04659 -0.0193 0.0063 1.0000
15.500 1.4056 0.05586 0.05119 -0.0196 0.0061 1.0000
15.750 1.3934 0.06040 0.05587 -0.0201 0.0060 1.0000
16.000 1.3883 0.06419 0.05976 -0.0206 0.0059 1.0000
16.250 1.3821 0.06819 0.06387 -0.0214 0.0059 1.0000
16.500 1.3824 0.07150 0.06727 -0.0222 0.0058 1.0000
16.750 1.3747 0.07588 0.07177 -0.0232 0.0058 1.0000
17.000 1.3687 0.08013 0.07612 -0.0243 0.0057 1.0000
17.250 1.3618 0.08464 0.08075 -0.0256 0.0056 1.0000
17.500 1.3529 0.08952 0.08574 -0.0271 0.0056 1.0000
17.750 1.3461 0.09416 0.09048 -0.0287 0.0055 1.0000
18.000 1.3383 0.09909 0.09551 -0.0305 0.0054 1.0000
18.250 1.3308 0.10407 0.10059 -0.0324 0.0054 1.0000
18.500 1.3235 0.10916 0.10579 -0.0346 0.0052 1.0000
18.750 1.3114 0.11503 0.11178 -0.0370 0.0052 1.0000
19.000 1.3043 0.12031 0.11714 -0.0394 0.0051 1.0000
|
Polar data table (+)
Polar graphs
<< Back to K3311 (smoothed) (k3311sm-il)