GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 50,000 Max Cl/Cd: 21.1 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k2-il-50000-n5.txt Download as CSV file: xf-k2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-2 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6414 0.09633 0.08796 -0.0333 1.0000 0.0557
-9.500 -0.6582 0.08940 0.08103 -0.0371 1.0000 0.0549
-9.250 -0.6811 0.08301 0.07461 -0.0401 1.0000 0.0542
-9.000 -0.7072 0.07765 0.06918 -0.0413 1.0000 0.0535
-8.750 -0.7342 0.07341 0.06488 -0.0404 1.0000 0.0530
-8.500 -0.7573 0.06956 0.06090 -0.0388 1.0000 0.0526
-8.250 -0.7730 0.06574 0.05687 -0.0374 1.0000 0.0524
-8.000 -0.7822 0.06212 0.05301 -0.0357 1.0000 0.0523
-7.750 -0.7864 0.05859 0.04917 -0.0341 1.0000 0.0522
-7.500 -0.7859 0.05520 0.04547 -0.0325 1.0000 0.0522
-7.250 -0.7811 0.05201 0.04194 -0.0310 1.0000 0.0524
-7.000 -0.7724 0.04902 0.03861 -0.0296 1.0000 0.0527
-6.750 -0.7604 0.04622 0.03547 -0.0283 1.0000 0.0532
-6.500 -0.7458 0.04368 0.03260 -0.0271 1.0000 0.0541
-6.250 -0.7293 0.04138 0.02991 -0.0260 1.0000 0.0559
-6.000 -0.7108 0.03922 0.02726 -0.0248 1.0000 0.0579
-5.750 -0.6910 0.03731 0.02530 -0.0239 1.0000 0.0597
-5.500 -0.6699 0.03564 0.02352 -0.0228 1.0000 0.0616
-5.250 -0.6478 0.03408 0.02179 -0.0215 1.0000 0.0638
-5.000 -0.6252 0.03276 0.02023 -0.0201 1.0000 0.0673
-4.750 -0.6036 0.03150 0.01905 -0.0188 1.0000 0.0712
-4.500 -0.5814 0.03045 0.01794 -0.0172 1.0000 0.0755
-4.250 -0.5595 0.02945 0.01684 -0.0156 1.0000 0.0808
-4.000 -0.5394 0.02848 0.01589 -0.0141 1.0000 0.0880
-3.750 -0.5199 0.02745 0.01488 -0.0126 1.0000 0.0962
-3.500 -0.5006 0.02640 0.01389 -0.0113 1.0000 0.1089
-3.250 -0.4815 0.02519 0.01285 -0.0103 1.0000 0.1300
-3.000 -0.4632 0.02346 0.01175 -0.0098 1.0000 0.1924
-2.750 -0.4526 0.02105 0.01118 -0.0079 1.0000 0.4449
-2.500 -0.4506 0.02227 0.01332 0.0024 1.0000 0.6205
-2.000 -0.4224 0.02459 0.01543 0.0125 1.0000 0.7594
-1.750 -0.4126 0.02588 0.01665 0.0194 1.0000 0.8047
-1.500 -0.3972 0.02633 0.01696 0.0239 1.0000 0.8339
-1.250 -0.3784 0.02619 0.01667 0.0263 1.0000 0.8509
-1.000 -0.3586 0.02595 0.01627 0.0283 1.0000 0.8665
-0.750 -0.3373 0.02563 0.01583 0.0299 1.0000 0.8813
-0.500 -0.3154 0.02526 0.01534 0.0312 1.0000 0.8950
-0.250 -0.2911 0.02484 0.01482 0.0319 1.0000 0.9065
0.000 -0.2665 0.02442 0.01430 0.0322 1.0000 0.9160
0.250 -0.2438 0.02402 0.01383 0.0327 1.0000 0.9246
0.500 -0.2222 0.02364 0.01341 0.0334 1.0000 0.9327
0.750 -0.1954 0.02330 0.01302 0.0330 1.0000 0.9390
1.000 -0.1736 0.02299 0.01269 0.0334 1.0000 0.9458
1.250 -0.1464 0.02272 0.01242 0.0329 1.0000 0.9514
1.500 -0.1223 0.02248 0.01220 0.0328 1.0000 0.9573
1.750 -0.0946 0.02230 0.01205 0.0320 1.0000 0.9623
2.000 -0.0683 0.02216 0.01197 0.0315 1.0000 0.9673
2.250 -0.0395 0.02207 0.01195 0.0304 1.0000 0.9719
2.500 -0.0126 0.02203 0.01200 0.0296 1.0000 0.9766
2.750 0.0158 0.02204 0.01214 0.0284 1.0000 0.9812
3.000 0.0424 0.02209 0.01233 0.0275 1.0000 0.9860
3.250 0.0922 0.02244 0.01288 0.0223 0.9885 0.9872
3.500 0.1699 0.02267 0.01339 0.0127 0.9539 0.9848
3.750 0.2369 0.02211 0.01315 0.0062 0.9053 0.9831
4.000 0.2805 0.02137 0.01268 0.0045 0.8467 0.9843
4.250 0.3952 0.02051 0.01118 -0.0067 0.5447 0.9763
4.500 0.4188 0.02182 0.01145 -0.0057 0.3690 0.9786
4.750 0.4422 0.02291 0.01204 -0.0054 0.2834 0.9817
5.000 0.4676 0.02388 0.01270 -0.0054 0.2307 0.9848
5.250 0.4972 0.02476 0.01339 -0.0064 0.1836 0.9873
5.500 0.5268 0.02571 0.01417 -0.0073 0.1466 0.9901
5.750 0.5570 0.02679 0.01520 -0.0081 0.1158 0.9930
6.000 0.5874 0.02797 0.01641 -0.0089 0.0924 0.9957
6.250 0.6157 0.02918 0.01764 -0.0092 0.0782 0.9988
6.500 0.6374 0.03041 0.01898 -0.0082 0.0693 1.0000
6.750 0.6549 0.03165 0.02030 -0.0066 0.0640 1.0000
7.000 0.6716 0.03292 0.02176 -0.0047 0.0591 1.0000
7.250 0.6865 0.03427 0.02324 -0.0027 0.0555 1.0000
7.500 0.7010 0.03592 0.02518 -0.0005 0.0525 1.0000
7.750 0.7145 0.03756 0.02703 0.0016 0.0508 1.0000
8.000 0.7278 0.03931 0.02891 0.0036 0.0493 1.0000
8.250 0.7386 0.04199 0.03215 0.0059 0.0477 1.0000
8.500 0.7486 0.04460 0.03519 0.0079 0.0460 1.0000
8.750 0.7596 0.04693 0.03781 0.0094 0.0444 1.0000
9.000 0.7732 0.04888 0.03988 0.0103 0.0430 1.0000
9.250 0.7774 0.05250 0.04396 0.0119 0.0424 1.0000
9.500 0.7777 0.05654 0.04847 0.0133 0.0422 1.0000
9.750 0.7739 0.06084 0.05318 0.0144 0.0422 1.0000
10.000 0.7663 0.06531 0.05799 0.0150 0.0422 1.0000
10.250 0.7546 0.06977 0.06270 0.0152 0.0424 1.0000
10.500 0.7408 0.07457 0.06771 0.0144 0.0425 1.0000
10.750 0.7272 0.07989 0.07317 0.0121 0.0428 1.0000
11.000 0.6824 0.09510 0.08862 -0.0014 0.0448 1.0000
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Polar data table (+)
Polar graphs
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