K3311 (original) (k3311-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 500,000 Max Cl/Cd: 100.2 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311-il-500000-n5.txt Download as CSV file: xf-k3311-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4097 0.09221 0.08990 -0.0385 1.0000 0.0108
-10.000 -0.4239 0.08527 0.08300 -0.0414 1.0000 0.0113
-9.500 -0.5844 0.04022 0.03763 -0.0731 0.9883 0.0118
-9.250 -0.5644 0.03775 0.03499 -0.0759 0.9822 0.0120
-9.000 -0.5409 0.03601 0.03312 -0.0780 0.9765 0.0122
-8.750 -0.5167 0.03452 0.03148 -0.0797 0.9702 0.0126
-8.500 -0.4912 0.03167 0.02836 -0.0825 0.9635 0.0131
-8.250 -0.4724 0.02681 0.02292 -0.0845 0.9517 0.0145
-8.000 -0.4492 0.02301 0.01838 -0.0857 0.9384 0.0156
-7.750 -0.4214 0.02153 0.01676 -0.0869 0.9258 0.0161
-7.500 -0.3929 0.02097 0.01612 -0.0877 0.9149 0.0166
-7.250 -0.3658 0.02035 0.01538 -0.0880 0.9036 0.0171
-7.000 -0.3408 0.01954 0.01439 -0.0879 0.8911 0.0177
-6.750 -0.3169 0.01853 0.01316 -0.0875 0.8786 0.0184
-6.500 -0.2928 0.01763 0.01204 -0.0870 0.8665 0.0190
-6.250 -0.2680 0.01698 0.01118 -0.0865 0.8550 0.0197
-6.000 -0.2429 0.01651 0.01053 -0.0860 0.8434 0.0203
-5.750 -0.2179 0.01602 0.00986 -0.0855 0.8307 0.0206
-5.500 -0.1942 0.01494 0.00860 -0.0848 0.8172 0.0210
-5.250 -0.1707 0.01391 0.00745 -0.0841 0.8029 0.0216
-5.000 -0.1463 0.01332 0.00678 -0.0836 0.7894 0.0222
-4.750 -0.1213 0.01289 0.00625 -0.0831 0.7771 0.0229
-4.500 -0.0963 0.01244 0.00571 -0.0825 0.7661 0.0233
-4.000 -0.0458 0.01167 0.00476 -0.0815 0.7451 0.0241
-3.750 -0.0203 0.01133 0.00434 -0.0810 0.7346 0.0245
-3.500 0.0051 0.01103 0.00396 -0.0805 0.7235 0.0249
-3.250 0.0307 0.01076 0.00362 -0.0801 0.7125 0.0252
-3.000 0.0566 0.01051 0.00330 -0.0796 0.7025 0.0257
-2.750 0.0826 0.01032 0.00304 -0.0792 0.6936 0.0263
-2.500 0.1086 0.01014 0.00279 -0.0789 0.6851 0.0267
-2.250 0.1349 0.00997 0.00256 -0.0785 0.6772 0.0270
-2.000 0.1612 0.00984 0.00235 -0.0782 0.6699 0.0273
-1.750 0.1879 0.00972 0.00218 -0.0779 0.6632 0.0276
-1.500 0.2143 0.00961 0.00199 -0.0776 0.6554 0.0286
-1.250 0.2411 0.00951 0.00184 -0.0773 0.6470 0.0298
-1.000 0.2676 0.00947 0.00173 -0.0770 0.6374 0.0313
-0.750 0.2945 0.00940 0.00165 -0.0767 0.6270 0.0333
-0.500 0.3215 0.00934 0.00158 -0.0765 0.6180 0.0362
-0.250 0.3475 0.00914 0.00151 -0.0762 0.6088 0.0935
0.000 0.3695 0.00826 0.00145 -0.0756 0.5992 0.3637
0.250 0.3938 0.00795 0.00148 -0.0750 0.5888 0.4869
0.500 0.4190 0.00785 0.00150 -0.0745 0.5784 0.5458
1.000 0.4683 0.00761 0.00159 -0.0732 0.5595 0.6691
1.250 0.4926 0.00755 0.00165 -0.0724 0.5506 0.7200
1.500 0.5161 0.00743 0.00172 -0.0713 0.5416 0.7870
1.750 0.5810 0.00719 0.00183 -0.0793 0.5276 0.9794
2.000 0.6170 0.00733 0.00189 -0.0812 0.5157 1.0000
2.500 0.6668 0.00756 0.00204 -0.0800 0.4985 1.0000
3.000 0.7170 0.00780 0.00222 -0.0789 0.4837 1.0000
3.250 0.7418 0.00794 0.00232 -0.0782 0.4759 1.0000
3.500 0.7669 0.00806 0.00242 -0.0777 0.4656 1.0000
3.750 0.7917 0.00822 0.00255 -0.0771 0.4541 1.0000
4.000 0.8164 0.00838 0.00267 -0.0765 0.4420 1.0000
4.250 0.8410 0.00854 0.00281 -0.0759 0.4305 1.0000
4.500 0.8656 0.00871 0.00295 -0.0753 0.4165 1.0000
4.750 0.8900 0.00890 0.00311 -0.0747 0.4006 1.0000
5.000 0.9138 0.00912 0.00328 -0.0740 0.3809 1.0000
5.250 0.9370 0.00939 0.00348 -0.0732 0.3614 1.0000
5.750 0.9826 0.01000 0.00397 -0.0714 0.3227 1.0000
6.000 1.0044 0.01038 0.00426 -0.0705 0.3007 1.0000
6.250 1.0262 0.01076 0.00456 -0.0695 0.2763 1.0000
6.500 1.0450 0.01135 0.00495 -0.0681 0.2360 1.0000
6.750 1.0622 0.01206 0.00542 -0.0664 0.1936 1.0000
7.000 1.0783 0.01283 0.00595 -0.0647 0.1478 1.0000
7.250 1.0939 0.01362 0.00653 -0.0628 0.1102 1.0000
7.500 1.1114 0.01425 0.00705 -0.0613 0.0895 1.0000
7.750 1.1272 0.01497 0.00765 -0.0594 0.0618 1.0000
8.000 1.1386 0.01595 0.00842 -0.0570 0.0308 1.0000
8.250 1.1534 0.01666 0.00908 -0.0550 0.0202 1.0000
8.500 1.1699 0.01722 0.00966 -0.0532 0.0166 1.0000
8.750 1.1837 0.01781 0.01028 -0.0510 0.0143 1.0000
9.000 1.1975 0.01837 0.01089 -0.0487 0.0132 1.0000
9.250 1.2113 0.01893 0.01153 -0.0466 0.0122 1.0000
9.500 1.2240 0.01957 0.01222 -0.0444 0.0112 1.0000
9.750 1.2351 0.02033 0.01302 -0.0421 0.0104 1.0000
10.000 1.2431 0.02129 0.01407 -0.0394 0.0097 1.0000
10.250 1.2542 0.02210 0.01495 -0.0374 0.0094 1.0000
10.500 1.2643 0.02300 0.01593 -0.0353 0.0091 1.0000
10.750 1.2733 0.02400 0.01703 -0.0333 0.0087 1.0000
11.000 1.2815 0.02511 0.01823 -0.0314 0.0084 1.0000
11.250 1.2891 0.02633 0.01952 -0.0296 0.0081 1.0000
11.500 1.2970 0.02757 0.02084 -0.0280 0.0077 1.0000
11.750 1.3036 0.02897 0.02231 -0.0265 0.0074 1.0000
12.000 1.3071 0.03070 0.02412 -0.0249 0.0071 1.0000
12.250 1.3046 0.03306 0.02658 -0.0233 0.0068 1.0000
12.500 1.3094 0.03489 0.02850 -0.0223 0.0067 1.0000
12.750 1.3111 0.03709 0.03081 -0.0214 0.0066 1.0000
13.000 1.3155 0.03911 0.03294 -0.0207 0.0064 1.0000
13.250 1.3182 0.04138 0.03532 -0.0202 0.0063 1.0000
13.500 1.3186 0.04396 0.03801 -0.0197 0.0061 1.0000
13.750 1.3172 0.04680 0.04096 -0.0194 0.0060 1.0000
14.000 1.3176 0.04952 0.04379 -0.0193 0.0059 1.0000
14.250 1.3169 0.05246 0.04683 -0.0193 0.0058 1.0000
14.500 1.3161 0.05552 0.05000 -0.0195 0.0055 1.0000
14.750 1.3143 0.05880 0.05338 -0.0198 0.0054 1.0000
15.000 1.3115 0.06228 0.05697 -0.0203 0.0054 1.0000
15.250 1.3103 0.06570 0.06048 -0.0210 0.0052 1.0000
15.500 1.3043 0.06980 0.06471 -0.0218 0.0053 1.0000
15.750 1.3010 0.07367 0.06868 -0.0229 0.0052 1.0000
16.000 1.2958 0.07788 0.07300 -0.0240 0.0052 1.0000
16.250 1.2919 0.08208 0.07732 -0.0254 0.0050 1.0000
16.500 1.2860 0.08662 0.08198 -0.0268 0.0050 1.0000
16.750 1.2798 0.09131 0.08677 -0.0286 0.0049 1.0000
17.000 1.2739 0.09606 0.09163 -0.0303 0.0049 1.0000
17.250 1.2665 0.10114 0.09682 -0.0323 0.0048 1.0000
17.500 1.2593 0.10635 0.10214 -0.0346 0.0048 1.0000
17.750 1.2503 0.11185 0.10776 -0.0369 0.0047 1.0000
18.000 1.2424 0.11734 0.11337 -0.0394 0.0047 1.0000
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Polar data table (+)
Polar graphs
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