K3311 (original) (k3311-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 200,000 Max Cl/Cd: 76.24 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311-il-200000-n5.txt Download as CSV file: xf-k3311-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3803 0.08763 0.08410 -0.0412 1.0000 0.0237
-9.000 -0.3874 0.08309 0.07963 -0.0427 1.0000 0.0231
-8.750 -0.3996 0.07807 0.07469 -0.0444 1.0000 0.0225
-8.250 -0.4687 0.05711 0.05370 -0.0579 0.9963 0.0206
-8.000 -0.4627 0.04828 0.04447 -0.0666 0.9856 0.0209
-7.750 -0.4437 0.04512 0.04120 -0.0698 0.9777 0.0216
-7.500 -0.4175 0.04374 0.03975 -0.0723 0.9709 0.0226
-7.250 -0.3941 0.03948 0.03513 -0.0760 0.9632 0.0239
-7.000 -0.3742 0.03465 0.02979 -0.0781 0.9526 0.0246
-6.750 -0.3510 0.03073 0.02535 -0.0795 0.9431 0.0252
-6.500 -0.3225 0.02797 0.02204 -0.0808 0.9352 0.0266
-6.250 -0.2956 0.02646 0.02006 -0.0812 0.9251 0.0275
-6.000 -0.2683 0.02365 0.01684 -0.0821 0.9175 0.0280
-5.750 -0.2413 0.02173 0.01465 -0.0824 0.9081 0.0286
-5.500 -0.2127 0.02038 0.01314 -0.0830 0.8995 0.0296
-5.250 -0.1830 0.01938 0.01198 -0.0836 0.8907 0.0309
-5.000 -0.1551 0.01837 0.01080 -0.0836 0.8803 0.0317
-4.750 -0.1266 0.01740 0.00966 -0.0837 0.8705 0.0322
-4.500 -0.0985 0.01656 0.00868 -0.0837 0.8604 0.0327
-4.250 -0.0722 0.01586 0.00787 -0.0833 0.8492 0.0332
-4.000 -0.0459 0.01523 0.00715 -0.0830 0.8381 0.0338
-3.750 -0.0196 0.01473 0.00655 -0.0826 0.8268 0.0348
-3.500 0.0066 0.01430 0.00603 -0.0822 0.8152 0.0359
-3.250 0.0320 0.01387 0.00552 -0.0816 0.8033 0.0363
-3.000 0.0575 0.01344 0.00501 -0.0811 0.7924 0.0368
-2.750 0.0833 0.01304 0.00450 -0.0807 0.7822 0.0376
-2.500 0.1094 0.01275 0.00410 -0.0803 0.7719 0.0388
-2.250 0.1356 0.01253 0.00379 -0.0799 0.7613 0.0403
-2.000 0.1620 0.01236 0.00351 -0.0795 0.7515 0.0423
-1.750 0.1886 0.01222 0.00329 -0.0791 0.7418 0.0452
-1.500 0.2147 0.01204 0.00312 -0.0787 0.7315 0.0550
-1.250 0.2370 0.01118 0.00294 -0.0781 0.7219 0.2459
-1.000 0.2580 0.01044 0.00293 -0.0771 0.7124 0.4610
-0.750 0.2822 0.01024 0.00294 -0.0763 0.7026 0.5424
-0.500 0.3062 0.01007 0.00293 -0.0753 0.6936 0.6152
-0.250 0.3307 0.00996 0.00291 -0.0744 0.6840 0.6638
0.000 0.3544 0.00983 0.00293 -0.0733 0.6735 0.7250
0.250 0.3801 0.00962 0.00295 -0.0722 0.6633 0.8257
0.500 0.4520 0.00948 0.00290 -0.0812 0.6525 0.9789
0.750 0.4877 0.00958 0.00292 -0.0830 0.6426 1.0000
1.000 0.5121 0.00968 0.00294 -0.0823 0.6338 1.0000
1.250 0.5366 0.00980 0.00297 -0.0817 0.6249 1.0000
1.500 0.5612 0.00990 0.00303 -0.0810 0.6150 1.0000
1.750 0.5859 0.01001 0.00308 -0.0804 0.6057 1.0000
2.000 0.6107 0.01012 0.00314 -0.0798 0.5964 1.0000
2.250 0.6356 0.01023 0.00322 -0.0792 0.5866 1.0000
2.500 0.6605 0.01036 0.00330 -0.0786 0.5771 1.0000
2.750 0.6851 0.01050 0.00337 -0.0779 0.5664 1.0000
3.000 0.7096 0.01065 0.00348 -0.0772 0.5546 1.0000
3.250 0.7344 0.01081 0.00360 -0.0766 0.5440 1.0000
3.500 0.7591 0.01099 0.00374 -0.0760 0.5347 1.0000
3.750 0.7840 0.01116 0.00391 -0.0754 0.5249 1.0000
4.000 0.8089 0.01134 0.00409 -0.0749 0.5155 1.0000
4.250 0.8336 0.01154 0.00427 -0.0743 0.5065 1.0000
4.500 0.8583 0.01173 0.00448 -0.0737 0.4961 1.0000
4.750 0.8825 0.01194 0.00471 -0.0730 0.4847 1.0000
5.000 0.9065 0.01216 0.00493 -0.0723 0.4729 1.0000
5.250 0.9300 0.01239 0.00515 -0.0715 0.4588 1.0000
5.500 0.9531 0.01262 0.00541 -0.0706 0.4425 1.0000
5.750 0.9759 0.01287 0.00567 -0.0697 0.4245 1.0000
6.000 0.9988 0.01313 0.00594 -0.0689 0.4078 1.0000
6.250 1.0216 0.01340 0.00624 -0.0680 0.3927 1.0000
6.500 1.0437 0.01371 0.00658 -0.0670 0.3763 1.0000
6.750 1.0643 0.01409 0.00693 -0.0658 0.3570 1.0000
7.000 1.0830 0.01456 0.00733 -0.0643 0.3303 1.0000
7.250 1.0986 0.01521 0.00781 -0.0623 0.2928 1.0000
7.500 1.1119 0.01600 0.00836 -0.0602 0.2459 1.0000
7.750 1.1242 0.01689 0.00904 -0.0579 0.2029 1.0000
8.000 1.1365 0.01780 0.00976 -0.0557 0.1634 1.0000
8.250 1.1455 0.01890 0.01061 -0.0531 0.1217 1.0000
8.500 1.1537 0.02001 0.01154 -0.0503 0.0908 1.0000
8.750 1.1581 0.02120 0.01253 -0.0470 0.0552 1.0000
9.000 1.1607 0.02250 0.01367 -0.0435 0.0351 1.0000
9.250 1.1672 0.02361 0.01480 -0.0406 0.0280 1.0000
9.500 1.1736 0.02478 0.01602 -0.0379 0.0241 1.0000
9.750 1.1819 0.02585 0.01721 -0.0357 0.0216 1.0000
10.000 1.1874 0.02717 0.01859 -0.0333 0.0196 1.0000
10.250 1.1914 0.02864 0.02017 -0.0310 0.0185 1.0000
10.500 1.1974 0.03005 0.02172 -0.0291 0.0177 1.0000
10.750 1.2015 0.03167 0.02347 -0.0273 0.0168 1.0000
11.000 1.2054 0.03339 0.02530 -0.0257 0.0163 1.0000
11.250 1.2083 0.03528 0.02729 -0.0243 0.0154 1.0000
11.500 1.2103 0.03735 0.02949 -0.0231 0.0149 1.0000
11.750 1.2103 0.03969 0.03191 -0.0220 0.0142 1.0000
12.000 1.2056 0.04261 0.03491 -0.0210 0.0136 1.0000
12.250 1.2088 0.04486 0.03730 -0.0203 0.0132 1.0000
12.500 1.2099 0.04739 0.03994 -0.0197 0.0130 1.0000
12.750 1.2114 0.04996 0.04264 -0.0192 0.0126 1.0000
13.000 1.2127 0.05258 0.04539 -0.0188 0.0124 1.0000
13.250 1.2139 0.05529 0.04822 -0.0184 0.0121 1.0000
13.500 1.2151 0.05807 0.05111 -0.0182 0.0118 1.0000
13.750 1.2163 0.06091 0.05408 -0.0180 0.0115 1.0000
14.000 1.2176 0.06383 0.05712 -0.0180 0.0113 1.0000
14.250 1.2183 0.06688 0.06032 -0.0182 0.0110 1.0000
14.500 1.2178 0.07015 0.06369 -0.0187 0.0106 1.0000
14.750 1.2169 0.07355 0.06719 -0.0192 0.0104 1.0000
15.000 1.2160 0.07703 0.07079 -0.0199 0.0102 1.0000
15.250 1.2127 0.08089 0.07473 -0.0205 0.0098 1.0000
15.500 1.2107 0.08473 0.07873 -0.0212 0.0098 1.0000
15.750 1.2051 0.08929 0.08347 -0.0228 0.0096 1.0000
16.000 1.1994 0.09400 0.08837 -0.0245 0.0095 1.0000
16.250 1.1912 0.09934 0.09393 -0.0268 0.0093 1.0000
16.500 1.1835 0.10466 0.09943 -0.0291 0.0093 1.0000
16.750 1.1729 0.11074 0.10572 -0.0320 0.0092 1.0000
17.000 1.1628 0.11691 0.11208 -0.0351 0.0092 1.0000
17.250 1.1513 0.12356 0.11892 -0.0388 0.0092 1.0000
17.500 1.1385 0.13078 0.12633 -0.0429 0.0091 1.0000
17.750 1.1253 0.13835 0.13408 -0.0474 0.0091 1.0000
18.000 1.1113 0.14643 0.14234 -0.0523 0.0092 1.0000
18.250 1.0961 0.15524 0.15131 -0.0579 0.0092 1.0000
18.500 1.0793 0.16495 0.16118 -0.0640 0.0092 1.0000
18.750 1.0623 0.17524 0.17159 -0.0704 0.0094 1.0000
19.000 1.0403 0.18819 0.18465 -0.0781 0.0095 1.0000
19.250 1.0182 0.20261 0.19911 -0.0859 0.0097 1.0000
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