K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: K3311 (smoothed) (k3311sm-il) Reynolds number: 50,000 Max Cl/Cd: 33.89 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3311sm-il-50000.txt Download as CSV file: xf-k3311sm-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3715 0.12528 0.11816 -0.0282 1.0000 0.1952
-10.000 -0.3515 0.11994 0.11282 -0.0270 1.0000 0.2026
-9.750 -0.3662 0.11944 0.11245 -0.0285 1.0000 0.2100
-9.500 -0.3482 0.11465 0.10766 -0.0272 1.0000 0.2220
-9.250 -0.3425 0.11138 0.10445 -0.0268 1.0000 0.2314
-9.000 -0.3599 0.11100 0.10422 -0.0277 1.0000 0.2397
-8.750 -0.3467 0.10705 0.10027 -0.0264 1.0000 0.2533
-8.500 -0.3353 0.10333 0.09660 -0.0253 1.0000 0.2648
-8.250 -0.3335 0.10053 0.09388 -0.0245 1.0000 0.2755
-8.000 -0.3401 0.09853 0.09200 -0.0238 1.0000 0.2870
-7.750 -0.3579 0.09798 0.09161 -0.0225 1.0000 0.2992
-7.500 -0.3512 0.09489 0.08859 -0.0208 1.0000 0.3136
-7.250 -0.3479 0.09215 0.08594 -0.0188 1.0000 0.3281
-7.000 -0.3503 0.08990 0.08379 -0.0165 1.0000 0.3430
-6.750 -0.3540 0.08783 0.08184 -0.0138 1.0000 0.3580
-6.500 -0.3630 0.08621 0.08037 -0.0104 1.0000 0.3732
-6.250 -0.3401 0.08223 0.07636 -0.0082 1.0000 0.3990
-6.000 -0.3571 0.08136 0.07567 -0.0036 1.0000 0.4164
-5.750 -0.3768 0.08063 0.07512 0.0015 1.0000 0.4324
-5.500 -0.3580 0.07710 0.07158 0.0040 1.0000 0.4583
-5.250 -0.3871 0.07710 0.07176 0.0103 1.0000 0.4771
-4.500 -0.4175 0.05071 0.04400 -0.0364 1.0000 0.1681
-4.250 -0.3968 0.04618 0.03886 -0.0379 1.0000 0.1500
-4.000 -0.3783 0.04289 0.03526 -0.0380 1.0000 0.1447
-3.750 -0.3543 0.03966 0.03116 -0.0386 1.0000 0.1357
-3.500 -0.3334 0.03718 0.02831 -0.0382 1.0000 0.1328
-3.250 -0.3116 0.03510 0.02578 -0.0377 1.0000 0.1319
-3.000 -0.2903 0.03361 0.02377 -0.0370 1.0000 0.1356
-2.750 -0.2691 0.03213 0.02196 -0.0363 1.0000 0.1392
-2.500 -0.2485 0.03089 0.02059 -0.0355 1.0000 0.1429
-2.250 -0.2276 0.03003 0.01948 -0.0346 1.0000 0.1503
-2.000 -0.2069 0.02919 0.01864 -0.0339 1.0000 0.1624
-1.750 -0.1866 0.02848 0.01788 -0.0329 1.0000 0.1753
-1.500 -0.1601 0.02788 0.01734 -0.0333 0.9985 0.2062
-1.250 -0.1116 0.02394 0.01698 -0.0339 0.9923 1.0000
-1.000 -0.0643 0.02497 0.01710 -0.0386 0.9806 1.0000
-0.750 -0.0197 0.02597 0.01752 -0.0430 0.9693 1.0000
-0.500 0.0221 0.02689 0.01800 -0.0469 0.9574 1.0000
-0.250 0.0579 0.02768 0.01845 -0.0497 0.9453 1.0000
0.000 0.0929 0.02850 0.01896 -0.0522 0.9334 1.0000
0.250 0.1284 0.02934 0.01955 -0.0547 0.9218 1.0000
0.500 0.1661 0.03021 0.02019 -0.0576 0.9104 1.0000
0.750 0.2034 0.03105 0.02083 -0.0602 0.8991 1.0000
1.000 0.2306 0.03182 0.02144 -0.0612 0.8868 1.0000
1.250 0.2583 0.03265 0.02214 -0.0622 0.8751 1.0000
1.500 0.2891 0.03350 0.02286 -0.0636 0.8635 1.0000
1.750 0.3245 0.03434 0.02360 -0.0657 0.8525 1.0000
2.000 0.3562 0.03516 0.02434 -0.0671 0.8408 1.0000
2.250 0.3778 0.03607 0.02519 -0.0670 0.8286 1.0000
2.500 0.4021 0.03699 0.02607 -0.0673 0.8166 1.0000
2.750 0.4296 0.03791 0.02695 -0.0680 0.8050 1.0000
3.000 0.4629 0.03873 0.02777 -0.0694 0.7935 1.0000
3.250 0.4941 0.03955 0.02858 -0.0704 0.7818 1.0000
3.500 0.5125 0.04062 0.02966 -0.0698 0.7690 1.0000
3.750 0.5321 0.04173 0.03078 -0.0694 0.7565 1.0000
4.000 0.5547 0.04278 0.03187 -0.0693 0.7439 1.0000
4.250 0.5799 0.04377 0.03290 -0.0694 0.7314 1.0000
4.500 0.6089 0.04464 0.03383 -0.0698 0.7192 1.0000
4.750 0.6493 0.04506 0.03438 -0.0712 0.7076 1.0000
5.000 0.6647 0.04634 0.03572 -0.0702 0.6939 1.0000
5.250 0.6825 0.04757 0.03701 -0.0693 0.6801 1.0000
5.500 0.7008 0.04879 0.03831 -0.0685 0.6663 1.0000
5.750 0.7195 0.05001 0.03963 -0.0678 0.6523 1.0000
6.000 0.7394 0.05117 0.04092 -0.0670 0.6381 1.0000
6.250 0.7588 0.05237 0.04223 -0.0662 0.6239 1.0000
6.500 0.7789 0.05350 0.04348 -0.0654 0.6094 1.0000
6.750 0.7992 0.05462 0.04473 -0.0645 0.5948 1.0000
7.000 0.8212 0.05555 0.04584 -0.0635 0.5798 1.0000
7.250 0.8442 0.05637 0.04682 -0.0625 0.5647 1.0000
7.500 0.8706 0.05681 0.04745 -0.0614 0.5495 1.0000
7.750 0.9039 0.05649 0.04735 -0.0601 0.5341 1.0000
8.000 0.9673 0.05322 0.04449 -0.0592 0.5184 1.0000
8.250 1.0139 0.05136 0.04293 -0.0581 0.5007 1.0000
8.500 1.0032 0.05424 0.04589 -0.0549 0.4832 1.0000
8.750 1.1233 0.04498 0.03722 -0.0554 0.4545 1.0000
9.000 1.1965 0.03884 0.03118 -0.0542 0.4130 1.0000
9.250 1.2236 0.03645 0.02865 -0.0508 0.3712 1.0000
9.500 1.2283 0.03624 0.02836 -0.0462 0.3319 1.0000
9.750 1.2262 0.03670 0.02857 -0.0411 0.2895 1.0000
10.000 1.2175 0.03809 0.02961 -0.0359 0.2473 1.0000
10.250 1.2076 0.04011 0.03124 -0.0310 0.2110 1.0000
10.500 1.2019 0.04253 0.03338 -0.0271 0.1806 1.0000
10.750 1.2061 0.04519 0.03583 -0.0245 0.1551 1.0000
11.000 1.2175 0.04784 0.03834 -0.0227 0.1357 1.0000
11.250 1.2473 0.05116 0.04150 -0.0228 0.1190 1.0000
11.500 1.2506 0.05419 0.04493 -0.0205 0.1120 1.0000
11.750 1.2642 0.05758 0.04841 -0.0195 0.1043 1.0000
12.000 1.2597 0.06097 0.05220 -0.0171 0.1012 1.0000
12.250 1.2584 0.06473 0.05627 -0.0153 0.0988 1.0000
12.500 1.2609 0.06869 0.06043 -0.0140 0.0964 1.0000
12.750 1.2669 0.07343 0.06526 -0.0134 0.0937 1.0000
13.000 1.2470 0.07757 0.06970 -0.0118 0.0936 1.0000
13.250 1.2251 0.08223 0.07462 -0.0111 0.0937 1.0000
13.500 1.2028 0.08736 0.07998 -0.0112 0.0938 1.0000
13.750 1.1028 0.09915 0.09233 -0.0183 0.1025 1.0000
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Polar data table (+)
Polar graphs
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