K3311 (original) (k3311-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 50,000 Max Cl/Cd: 36.49 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311-il-50000-n5.txt Download as CSV file: xf-k3311-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: K3311 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3678 0.10643 0.09950 -0.0347 1.0000 0.1425
-9.000 -0.3921 0.10493 0.09821 -0.0379 1.0000 0.1447
-8.500 -0.3945 0.08924 0.08256 -0.0446 1.0000 0.0703
-8.250 -0.3940 0.08614 0.07953 -0.0436 1.0000 0.0688
-8.000 -0.4012 0.08294 0.07644 -0.0434 1.0000 0.0673
-7.750 -0.4099 0.07917 0.07278 -0.0443 1.0000 0.0659
-7.500 -0.4203 0.07510 0.06878 -0.0455 1.0000 0.0643
-7.250 -0.4327 0.07085 0.06456 -0.0464 1.0000 0.0627
-7.000 -0.4469 0.06612 0.05974 -0.0472 1.0000 0.0609
-6.750 -0.4636 0.06076 0.05385 -0.0485 1.0000 0.0584
-6.500 -0.4620 0.05760 0.05058 -0.0474 1.0000 0.0581
-6.250 -0.4601 0.05434 0.04703 -0.0465 1.0000 0.0583
-6.000 -0.4547 0.05147 0.04409 -0.0454 1.0000 0.0593
-5.750 -0.4467 0.04938 0.04197 -0.0442 1.0000 0.0609
-5.500 -0.4167 0.04549 0.03761 -0.0477 0.9924 0.0617
-5.250 -0.3837 0.04160 0.03304 -0.0510 0.9843 0.0614
-5.000 -0.3502 0.03849 0.02937 -0.0536 0.9760 0.0617
-4.750 -0.3171 0.03608 0.02650 -0.0556 0.9674 0.0628
-4.500 -0.2826 0.03418 0.02419 -0.0576 0.9591 0.0660
-4.250 -0.2468 0.03235 0.02189 -0.0594 0.9510 0.0682
-4.000 -0.2135 0.03077 0.01992 -0.0604 0.9421 0.0692
-3.750 -0.1754 0.02939 0.01821 -0.0622 0.9351 0.0706
-3.500 -0.1445 0.02824 0.01693 -0.0627 0.9256 0.0723
-3.250 -0.1064 0.02715 0.01575 -0.0646 0.9192 0.0758
-3.000 -0.0769 0.02646 0.01492 -0.0651 0.9089 0.0820
-2.750 -0.0411 0.02566 0.01398 -0.0667 0.9013 0.0890
-2.500 -0.0078 0.02496 0.01316 -0.0678 0.8926 0.0976
-2.000 0.0578 0.02245 0.01170 -0.0708 0.8767 0.3079
-1.750 0.0748 0.02143 0.01198 -0.0680 0.8670 0.6236
-1.500 0.1549 0.02043 0.01177 -0.0744 0.8658 0.9871
-1.250 0.1917 0.02043 0.01136 -0.0767 0.8573 1.0000
-1.000 0.2192 0.02049 0.01111 -0.0771 0.8467 1.0000
-0.750 0.2444 0.02063 0.01097 -0.0769 0.8353 1.0000
-0.500 0.2733 0.02073 0.01083 -0.0773 0.8256 1.0000
-0.250 0.3037 0.02081 0.01068 -0.0778 0.8162 1.0000
0.000 0.3285 0.02101 0.01069 -0.0775 0.8050 1.0000
0.250 0.3566 0.02116 0.01066 -0.0776 0.7954 1.0000
0.500 0.3874 0.02125 0.01058 -0.0780 0.7866 1.0000
0.750 0.4119 0.02149 0.01070 -0.0775 0.7756 1.0000
1.000 0.4397 0.02167 0.01076 -0.0775 0.7661 1.0000
1.250 0.4695 0.02177 0.01075 -0.0776 0.7570 1.0000
1.500 0.4932 0.02206 0.01096 -0.0769 0.7456 1.0000
1.750 0.5193 0.02228 0.01110 -0.0765 0.7351 1.0000
2.000 0.5499 0.02235 0.01110 -0.0766 0.7262 1.0000
2.250 0.5724 0.02268 0.01140 -0.0758 0.7144 1.0000
2.500 0.5968 0.02297 0.01166 -0.0751 0.7036 1.0000
2.750 0.6250 0.02314 0.01181 -0.0749 0.6945 1.0000
3.000 0.6512 0.02339 0.01205 -0.0745 0.6846 1.0000
3.250 0.6750 0.02375 0.01243 -0.0738 0.6740 1.0000
3.500 0.7022 0.02399 0.01269 -0.0735 0.6647 1.0000
3.750 0.7288 0.02426 0.01299 -0.0730 0.6549 1.0000
4.000 0.7508 0.02472 0.01351 -0.0721 0.6435 1.0000
4.250 0.7744 0.02511 0.01399 -0.0713 0.6326 1.0000
4.500 0.8005 0.02537 0.01430 -0.0708 0.6221 1.0000
4.750 0.8244 0.02569 0.01470 -0.0699 0.6106 1.0000
5.000 0.8455 0.02612 0.01525 -0.0688 0.5979 1.0000
5.250 0.8675 0.02649 0.01574 -0.0677 0.5855 1.0000
5.500 0.8906 0.02683 0.01618 -0.0667 0.5736 1.0000
5.750 0.9155 0.02708 0.01654 -0.0659 0.5620 1.0000
6.000 0.9428 0.02722 0.01682 -0.0653 0.5510 1.0000
6.250 0.9636 0.02770 0.01744 -0.0641 0.5377 1.0000
6.500 0.9848 0.02815 0.01806 -0.0629 0.5244 1.0000
6.750 1.0064 0.02859 0.01865 -0.0617 0.5107 1.0000
7.000 1.0280 0.02897 0.01922 -0.0605 0.4962 1.0000
7.250 1.0495 0.02921 0.01959 -0.0590 0.4795 1.0000
7.500 1.0710 0.02935 0.01982 -0.0574 0.4616 1.0000
7.750 1.0860 0.02986 0.02050 -0.0553 0.4423 1.0000
8.000 1.1011 0.03038 0.02120 -0.0532 0.4234 1.0000
8.250 1.1173 0.03087 0.02189 -0.0512 0.4052 1.0000
8.500 1.1343 0.03131 0.02246 -0.0493 0.3870 1.0000
8.750 1.1455 0.03208 0.02343 -0.0469 0.3672 1.0000
9.000 1.1558 0.03258 0.02396 -0.0441 0.3433 1.0000
9.250 1.1535 0.03345 0.02473 -0.0400 0.3117 1.0000
9.500 1.1459 0.03473 0.02590 -0.0357 0.2771 1.0000
9.750 1.1379 0.03642 0.02740 -0.0322 0.2414 1.0000
10.000 1.1314 0.03851 0.02935 -0.0296 0.2078 1.0000
10.250 1.1248 0.04097 0.03174 -0.0275 0.1754 1.0000
10.500 1.1165 0.04389 0.03449 -0.0259 0.1452 1.0000
10.750 1.1065 0.04728 0.03770 -0.0248 0.1200 1.0000
11.000 1.0965 0.05095 0.04121 -0.0240 0.1024 1.0000
11.250 1.0869 0.05481 0.04498 -0.0235 0.0886 1.0000
11.500 1.0804 0.05852 0.04869 -0.0231 0.0772 1.0000
11.750 1.0764 0.06204 0.05225 -0.0229 0.0690 1.0000
12.000 1.0710 0.06578 0.05595 -0.0229 0.0633 1.0000
12.250 1.0708 0.06902 0.05935 -0.0227 0.0580 1.0000
12.500 1.0702 0.07231 0.06270 -0.0226 0.0547 1.0000
12.750 1.0703 0.07556 0.06597 -0.0225 0.0519 1.0000
13.000 1.0743 0.07851 0.06916 -0.0221 0.0487 1.0000
13.250 1.0763 0.08175 0.07256 -0.0222 0.0459 1.0000
13.500 1.0778 0.08503 0.07594 -0.0224 0.0436 1.0000
13.750 1.0827 0.08791 0.07884 -0.0220 0.0418 1.0000
14.000 1.0866 0.09145 0.08271 -0.0221 0.0407 1.0000
14.250 1.0864 0.09569 0.08726 -0.0227 0.0399 1.0000
14.500 1.0813 0.10075 0.09261 -0.0242 0.0391 1.0000
14.750 1.0728 0.10650 0.09863 -0.0265 0.0386 1.0000
15.000 1.0614 0.11299 0.10537 -0.0295 0.0384 1.0000
15.250 1.0467 0.12046 0.11308 -0.0334 0.0384 1.0000
15.500 1.0291 0.12909 0.12192 -0.0383 0.0386 1.0000
15.750 1.0090 0.13905 0.13206 -0.0442 0.0391 1.0000
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Polar data table (+)
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