K3311 (original) (k3311-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.42 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311-il-1000000-n5.txt Download as CSV file: xf-k3311-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9215 0.03135 0.02885 -0.0753 1.0000 0.0075
-12.250 -0.9209 0.02777 0.02495 -0.0750 0.9985 0.0078
-12.000 -0.9028 0.02499 0.02188 -0.0765 0.9950 0.0081
-11.750 -0.8842 0.02271 0.01933 -0.0772 0.9912 0.0085
-11.500 -0.8612 0.02103 0.01744 -0.0779 0.9878 0.0088
-11.250 -0.8310 0.02069 0.01708 -0.0790 0.9858 0.0092
-11.000 -0.8023 0.02055 0.01694 -0.0794 0.9823 0.0095
-10.750 -0.7720 0.02061 0.01702 -0.0801 0.9789 0.0098
-10.500 -0.7406 0.02041 0.01681 -0.0812 0.9762 0.0102
-10.250 -0.7113 0.01969 0.01598 -0.0823 0.9727 0.0107
-10.000 -0.6847 0.01836 0.01445 -0.0831 0.9674 0.0113
-9.750 -0.6544 0.01713 0.01302 -0.0846 0.9628 0.0118
-9.500 -0.6226 0.01690 0.01274 -0.0857 0.9548 0.0121
-9.250 -0.5874 0.01684 0.01266 -0.0875 0.9444 0.0123
-9.000 -0.5547 0.01665 0.01240 -0.0887 0.9266 0.0126
-8.750 -0.5264 0.01656 0.01221 -0.0890 0.9065 0.0129
-8.500 -0.5014 0.01628 0.01181 -0.0886 0.8891 0.0132
-8.250 -0.4763 0.01612 0.01154 -0.0882 0.8752 0.0137
-8.000 -0.4526 0.01561 0.01089 -0.0876 0.8628 0.0143
-7.750 -0.4288 0.01506 0.01019 -0.0870 0.8511 0.0148
-7.500 -0.4044 0.01464 0.00963 -0.0865 0.8396 0.0152
-7.250 -0.3792 0.01442 0.00930 -0.0860 0.8268 0.0155
-7.000 -0.3541 0.01421 0.00898 -0.0856 0.8123 0.0156
-6.750 -0.3324 0.01318 0.00779 -0.0847 0.7960 0.0161
-6.500 -0.3080 0.01281 0.00733 -0.0842 0.7812 0.0164
-6.250 -0.2830 0.01254 0.00698 -0.0837 0.7681 0.0168
-6.000 -0.2575 0.01233 0.00669 -0.0833 0.7566 0.0171
-5.750 -0.2318 0.01202 0.00631 -0.0829 0.7460 0.0175
-5.500 -0.2064 0.01165 0.00585 -0.0825 0.7353 0.0179
-5.250 -0.1810 0.01131 0.00543 -0.0821 0.7237 0.0183
-5.000 -0.1555 0.01100 0.00503 -0.0816 0.7112 0.0187
-4.750 -0.1297 0.01075 0.00471 -0.0812 0.6989 0.0192
-4.500 -0.1039 0.01050 0.00437 -0.0809 0.6888 0.0196
-4.250 -0.0781 0.01025 0.00405 -0.0805 0.6806 0.0198
-4.000 -0.0518 0.01001 0.00376 -0.0801 0.6742 0.0201
-3.500 0.0010 0.00959 0.00324 -0.0796 0.6632 0.0204
-3.250 0.0276 0.00941 0.00302 -0.0793 0.6575 0.0206
-3.000 0.0541 0.00924 0.00280 -0.0790 0.6524 0.0207
-2.750 0.0807 0.00898 0.00250 -0.0788 0.6474 0.0208
-2.500 0.1070 0.00874 0.00221 -0.0784 0.6411 0.0211
-2.250 0.1336 0.00852 0.00194 -0.0782 0.6341 0.0218
-2.000 0.1603 0.00839 0.00176 -0.0779 0.6246 0.0224
-1.750 0.1874 0.00827 0.00160 -0.0777 0.6134 0.0229
-1.500 0.2142 0.00818 0.00148 -0.0775 0.6001 0.0234
-1.250 0.2411 0.00813 0.00136 -0.0773 0.5874 0.0241
-1.000 0.2680 0.00809 0.00128 -0.0770 0.5764 0.0248
-0.750 0.2949 0.00807 0.00121 -0.0768 0.5653 0.0257
-0.500 0.3218 0.00807 0.00116 -0.0766 0.5543 0.0264
-0.250 0.3489 0.00806 0.00112 -0.0764 0.5452 0.0270
0.000 0.3759 0.00807 0.00110 -0.0762 0.5369 0.0279
0.250 0.4031 0.00806 0.00108 -0.0761 0.5293 0.0317
0.500 0.4293 0.00795 0.00107 -0.0758 0.5211 0.0867
0.750 0.4526 0.00731 0.00106 -0.0752 0.5127 0.3242
1.000 0.4767 0.00701 0.00110 -0.0747 0.5031 0.4600
1.250 0.5021 0.00690 0.00116 -0.0743 0.4929 0.5325
1.500 0.5283 0.00686 0.00122 -0.0740 0.4837 0.5767
1.750 0.5539 0.00682 0.00129 -0.0735 0.4762 0.6260
2.000 0.5800 0.00676 0.00135 -0.0732 0.4705 0.6664
2.250 0.6055 0.00671 0.00142 -0.0727 0.4641 0.7136
2.500 0.6279 0.00653 0.00152 -0.0715 0.4580 0.8103
3.000 0.7244 0.00649 0.00174 -0.0807 0.4303 0.9983
3.250 0.7517 0.00661 0.00183 -0.0807 0.4181 1.0000
3.500 0.7768 0.00673 0.00191 -0.0801 0.4064 1.0000
3.750 0.8013 0.00689 0.00202 -0.0795 0.3914 1.0000
4.000 0.8254 0.00709 0.00214 -0.0788 0.3738 1.0000
4.250 0.8493 0.00730 0.00228 -0.0780 0.3558 1.0000
4.500 0.8729 0.00754 0.00244 -0.0773 0.3360 1.0000
4.750 0.8967 0.00778 0.00261 -0.0765 0.3193 1.0000
5.000 0.9204 0.00803 0.00279 -0.0758 0.3025 1.0000
5.250 0.9435 0.00832 0.00299 -0.0750 0.2820 1.0000
5.500 0.9660 0.00865 0.00322 -0.0741 0.2570 1.0000
5.750 0.9881 0.00901 0.00347 -0.0731 0.2310 1.0000
6.000 1.0082 0.00952 0.00380 -0.0718 0.1972 1.0000
6.250 1.0259 0.01020 0.00422 -0.0702 0.1486 1.0000
6.500 1.0435 0.01089 0.00468 -0.0686 0.1082 1.0000
6.750 1.0639 0.01135 0.00505 -0.0674 0.0896 1.0000
7.000 1.0847 0.01178 0.00541 -0.0662 0.0730 1.0000
7.250 1.1002 0.01258 0.00598 -0.0643 0.0369 1.0000
7.500 1.1185 0.01315 0.00647 -0.0628 0.0220 1.0000
7.750 1.1381 0.01362 0.00692 -0.0614 0.0153 1.0000
8.000 1.1585 0.01401 0.00731 -0.0603 0.0127 1.0000
8.250 1.1783 0.01442 0.00773 -0.0590 0.0109 1.0000
8.500 1.1974 0.01485 0.00818 -0.0576 0.0097 1.0000
8.750 1.2171 0.01522 0.00859 -0.0564 0.0092 1.0000
9.000 1.2358 0.01563 0.00904 -0.0550 0.0087 1.0000
9.250 1.2526 0.01606 0.00950 -0.0532 0.0082 1.0000
9.500 1.2672 0.01652 0.00999 -0.0510 0.0076 1.0000
9.750 1.2804 0.01705 0.01055 -0.0487 0.0071 1.0000
10.000 1.2934 0.01762 0.01116 -0.0464 0.0067 1.0000
10.250 1.3081 0.01811 0.01170 -0.0445 0.0064 1.0000
10.500 1.3218 0.01868 0.01233 -0.0425 0.0061 1.0000
10.750 1.3345 0.01932 0.01302 -0.0405 0.0058 1.0000
11.000 1.3469 0.02000 0.01375 -0.0386 0.0057 1.0000
11.250 1.3585 0.02075 0.01455 -0.0367 0.0054 1.0000
11.500 1.3698 0.02156 0.01540 -0.0348 0.0052 1.0000
11.750 1.3798 0.02248 0.01638 -0.0330 0.0050 1.0000
12.000 1.3874 0.02362 0.01759 -0.0310 0.0048 1.0000
12.250 1.3930 0.02496 0.01901 -0.0290 0.0046 1.0000
12.500 1.4023 0.02609 0.02021 -0.0276 0.0045 1.0000
12.750 1.4085 0.02753 0.02173 -0.0261 0.0045 1.0000
13.000 1.4170 0.02884 0.02312 -0.0249 0.0044 1.0000
13.250 1.4242 0.03033 0.02468 -0.0238 0.0043 1.0000
13.500 1.4291 0.03209 0.02653 -0.0227 0.0042 1.0000
13.750 1.4327 0.03405 0.02857 -0.0218 0.0041 1.0000
14.000 1.4376 0.03594 0.03055 -0.0211 0.0040 1.0000
14.250 1.4435 0.03781 0.03249 -0.0205 0.0038 1.0000
14.500 1.4453 0.04018 0.03495 -0.0201 0.0037 1.0000
14.750 1.4470 0.04259 0.03744 -0.0197 0.0036 1.0000
15.000 1.4467 0.04528 0.04023 -0.0195 0.0036 1.0000
15.250 1.4491 0.04775 0.04277 -0.0194 0.0035 1.0000
15.500 1.4498 0.05047 0.04558 -0.0194 0.0034 1.0000
15.750 1.4421 0.05433 0.04955 -0.0197 0.0034 1.0000
16.000 1.4442 0.05708 0.05236 -0.0200 0.0033 1.0000
16.250 1.4386 0.06090 0.05627 -0.0206 0.0032 1.0000
16.500 1.4335 0.06473 0.06022 -0.0214 0.0032 1.0000
16.750 1.4215 0.06967 0.06527 -0.0225 0.0031 1.0000
17.000 1.4152 0.07393 0.06963 -0.0237 0.0031 1.0000
17.250 1.4037 0.07903 0.07485 -0.0252 0.0031 1.0000
17.500 1.3897 0.08468 0.08062 -0.0270 0.0030 1.0000
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Polar data table (+)
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