K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: K3311 (smoothed) (k3311sm-il) Reynolds number: 200,000 Max Cl/Cd: 77.62 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3311sm-il-200000.txt Download as CSV file: xf-k3311sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3561 0.08731 0.08394 -0.0399 1.0000 0.0471
-8.250 -0.3611 0.08432 0.08100 -0.0403 1.0000 0.0482
-8.000 -0.3703 0.08145 0.07822 -0.0402 1.0000 0.0491
-7.750 -0.3886 0.07905 0.07592 -0.0390 1.0000 0.0500
-7.500 -0.4116 0.07733 0.07432 -0.0364 1.0000 0.0501
-7.250 -0.4312 0.07511 0.07218 -0.0350 1.0000 0.0500
-7.000 -0.4276 0.06613 0.06279 -0.0524 0.9923 0.0528
-6.750 -0.4114 0.05749 0.05395 -0.0596 0.9854 0.0542
-6.500 -0.3848 0.05404 0.05061 -0.0617 0.9810 0.0559
-6.250 -0.3572 0.05049 0.04697 -0.0654 0.9744 0.0588
-6.000 -0.3312 0.04467 0.04035 -0.0720 0.9646 0.0674
-5.750 -0.3006 0.04160 0.03751 -0.0743 0.9602 0.0713
-5.500 -0.2705 0.03784 0.03319 -0.0779 0.9534 0.0822
-5.250 -0.2396 0.03500 0.03036 -0.0799 0.9471 0.0866
-5.000 -0.2001 0.02514 0.01860 -0.0799 0.9431 0.0423
-4.750 -0.1691 0.02285 0.01596 -0.0804 0.9353 0.0422
-4.500 -0.1324 0.02080 0.01383 -0.0827 0.9308 0.0461
-4.250 -0.0950 0.01911 0.01188 -0.0842 0.9258 0.0479
-4.000 -0.0627 0.01785 0.01042 -0.0847 0.9176 0.0504
-3.750 -0.0258 0.01652 0.00894 -0.0861 0.9123 0.0548
-3.500 0.0020 0.01545 0.00791 -0.0859 0.9021 0.0587
-3.250 0.0319 0.01476 0.00715 -0.0860 0.8928 0.0647
-3.000 0.0615 0.01381 0.00621 -0.0862 0.8844 0.0732
-2.750 0.0864 0.01317 0.00556 -0.0854 0.8728 0.0846
-2.500 0.1117 0.01246 0.00495 -0.0847 0.8620 0.1202
-2.250 0.1269 0.01072 0.00472 -0.0828 0.8516 0.4957
-2.000 0.1499 0.01039 0.00466 -0.0813 0.8410 0.6054
-1.750 0.1726 0.01019 0.00460 -0.0798 0.8294 0.6726
-1.500 0.1960 0.01001 0.00453 -0.0783 0.8188 0.7319
-1.250 0.2201 0.00979 0.00445 -0.0766 0.8094 0.8008
-1.000 0.2540 0.00958 0.00441 -0.0768 0.7989 0.8932
-0.750 0.3150 0.00952 0.00425 -0.0832 0.7892 0.9497
-0.500 0.3701 0.00951 0.00406 -0.0887 0.7797 0.9813
-0.250 0.4146 0.00951 0.00390 -0.0926 0.7685 1.0000
0.000 0.4351 0.00958 0.00383 -0.0913 0.7569 1.0000
0.250 0.4578 0.00967 0.00379 -0.0904 0.7463 1.0000
0.500 0.4820 0.00977 0.00374 -0.0896 0.7364 1.0000
0.750 0.5051 0.00988 0.00376 -0.0887 0.7252 1.0000
1.000 0.5289 0.01000 0.00380 -0.0878 0.7145 1.0000
1.250 0.5535 0.01013 0.00382 -0.0871 0.7047 1.0000
1.500 0.5781 0.01026 0.00386 -0.0864 0.6945 1.0000
1.750 0.6021 0.01040 0.00395 -0.0856 0.6839 1.0000
2.000 0.6269 0.01055 0.00402 -0.0849 0.6742 1.0000
2.250 0.6521 0.01069 0.00409 -0.0843 0.6645 1.0000
2.500 0.6763 0.01084 0.00422 -0.0835 0.6538 1.0000
2.750 0.7012 0.01100 0.00434 -0.0828 0.6439 1.0000
3.000 0.7267 0.01116 0.00442 -0.0823 0.6345 1.0000
3.250 0.7509 0.01131 0.00459 -0.0815 0.6235 1.0000
3.500 0.7756 0.01148 0.00474 -0.0808 0.6131 1.0000
3.750 0.8009 0.01165 0.00486 -0.0803 0.6033 1.0000
4.000 0.8254 0.01181 0.00502 -0.0795 0.5923 1.0000
4.250 0.8497 0.01198 0.00522 -0.0788 0.5812 1.0000
4.500 0.8744 0.01216 0.00540 -0.0781 0.5706 1.0000
4.750 0.8993 0.01235 0.00555 -0.0775 0.5598 1.0000
5.000 0.9233 0.01252 0.00574 -0.0767 0.5479 1.0000
5.250 0.9470 0.01271 0.00598 -0.0759 0.5355 1.0000
5.500 0.9707 0.01290 0.00620 -0.0750 0.5228 1.0000
5.750 0.9941 0.01309 0.00641 -0.0741 0.5097 1.0000
6.000 1.0173 0.01330 0.00665 -0.0732 0.4961 1.0000
6.250 1.0402 0.01352 0.00691 -0.0722 0.4820 1.0000
6.500 1.0625 0.01374 0.00717 -0.0712 0.4668 1.0000
6.750 1.0842 0.01398 0.00743 -0.0700 0.4503 1.0000
7.000 1.1045 0.01423 0.00765 -0.0685 0.4306 1.0000
7.250 1.1234 0.01448 0.00793 -0.0669 0.4060 1.0000
7.500 1.1416 0.01482 0.00824 -0.0651 0.3809 1.0000
7.750 1.1592 0.01523 0.00861 -0.0634 0.3558 1.0000
8.000 1.1755 0.01572 0.00904 -0.0615 0.3285 1.0000
8.250 1.1906 0.01628 0.00957 -0.0594 0.2986 1.0000
8.500 1.2040 0.01695 0.01015 -0.0571 0.2657 1.0000
8.750 1.2144 0.01778 0.01083 -0.0545 0.2305 1.0000
9.000 1.2220 0.01878 0.01165 -0.0515 0.1900 1.0000
9.250 1.2232 0.02003 0.01263 -0.0476 0.1454 1.0000
9.500 1.2173 0.02171 0.01396 -0.0428 0.0974 1.0000
9.750 1.2100 0.02362 0.01561 -0.0382 0.0699 1.0000
10.000 1.2063 0.02541 0.01734 -0.0344 0.0572 1.0000
10.250 1.2082 0.02696 0.01894 -0.0316 0.0499 1.0000
10.500 1.2059 0.02888 0.02093 -0.0287 0.0458 1.0000
10.750 1.2090 0.03056 0.02271 -0.0266 0.0420 1.0000
11.000 1.2085 0.03261 0.02480 -0.0244 0.0392 1.0000
11.250 1.2039 0.03525 0.02744 -0.0221 0.0372 1.0000
11.500 1.2111 0.03694 0.02928 -0.0207 0.0355 1.0000
11.750 1.2173 0.03876 0.03120 -0.0195 0.0334 1.0000
12.000 1.2227 0.04071 0.03320 -0.0183 0.0316 1.0000
12.250 1.2285 0.04277 0.03529 -0.0171 0.0302 1.0000
12.500 1.2426 0.04517 0.03770 -0.0153 0.0286 1.0000
12.750 1.2522 0.04712 0.03986 -0.0143 0.0280 1.0000
13.000 1.2605 0.04925 0.04218 -0.0132 0.0271 1.0000
13.250 1.2656 0.05154 0.04466 -0.0124 0.0260 1.0000
13.500 1.2700 0.05392 0.04718 -0.0117 0.0249 1.0000
13.750 1.2728 0.05652 0.04992 -0.0111 0.0240 1.0000
14.000 1.2759 0.05938 0.05294 -0.0105 0.0236 1.0000
14.250 1.2772 0.06251 0.05623 -0.0101 0.0231 1.0000
14.500 1.2767 0.06601 0.05990 -0.0098 0.0227 1.0000
14.750 1.2726 0.07007 0.06415 -0.0097 0.0224 1.0000
15.000 1.2644 0.07435 0.06866 -0.0101 0.0224 1.0000
15.250 1.2528 0.07925 0.07379 -0.0108 0.0223 1.0000
15.500 1.2388 0.08433 0.07911 -0.0122 0.0223 1.0000
15.750 1.2231 0.08987 0.08487 -0.0141 0.0223 1.0000
16.000 1.2056 0.09593 0.09116 -0.0166 0.0224 1.0000
16.250 1.1847 0.10283 0.09832 -0.0202 0.0227 1.0000
16.500 1.1602 0.11107 0.10682 -0.0247 0.0230 1.0000
16.750 1.1210 0.12315 0.11925 -0.0325 0.0238 1.0000
17.000 1.0727 0.13911 0.13552 -0.0432 0.0248 1.0000
17.250 1.0155 0.16079 0.15737 -0.0573 0.0266 1.0000
17.500 0.9873 0.17581 0.17236 -0.0654 0.0281 1.0000
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