GRUMMAN K-3 AIRFOIL (k3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GRUMMAN K-3 AIRFOIL (k3-il) Reynolds number: 50,000 Max Cl/Cd: 24.89 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3-il-50000.txt Download as CSV file: xf-k3-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-3 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7479 0.07687 0.06820 -0.0333 0.9999 0.2555
-9.250 -0.8490 0.06220 0.05333 -0.0368 0.9999 0.2530
-9.000 -0.8859 0.05276 0.04325 -0.0408 0.9999 0.2571
-8.750 -0.8556 0.05440 0.04528 -0.0368 0.9999 0.2650
-8.500 -0.8593 0.04823 0.03851 -0.0407 0.9999 0.2741
-8.250 -0.8385 0.04830 0.03885 -0.0378 0.9999 0.2824
-8.000 -0.8245 0.04458 0.03474 -0.0405 0.9999 0.2944
-7.750 -0.8047 0.04476 0.03519 -0.0376 0.9999 0.3037
-7.500 -0.7855 0.04276 0.03306 -0.0384 0.9999 0.3164
-7.250 -0.7638 0.04107 0.03121 -0.0394 0.9999 0.3310
-7.000 -0.7457 0.04162 0.03206 -0.0359 0.9999 0.3413
-6.750 -0.7250 0.04091 0.03137 -0.0353 0.9999 0.3562
-6.500 -0.7040 0.04050 0.03097 -0.0345 0.9999 0.3729
-6.250 -0.6826 0.04025 0.03075 -0.0337 0.9999 0.3903
-6.000 -0.6684 0.04210 0.03287 -0.0278 0.9999 0.3992
-5.750 -0.6490 0.04235 0.03317 -0.0258 0.9999 0.4149
-5.500 -0.6292 0.04256 0.03338 -0.0240 0.9999 0.4319
-5.250 -0.6097 0.04296 0.03379 -0.0221 0.9999 0.4498
-5.000 -0.5972 0.04505 0.03603 -0.0156 0.9999 0.4581
-4.750 -0.5798 0.04570 0.03669 -0.0127 0.9999 0.4750
-4.500 -0.5621 0.04621 0.03719 -0.0102 0.9999 0.4934
-4.250 -0.5445 0.04666 0.03762 -0.0078 0.9999 0.5127
-4.000 -0.5268 0.04703 0.03797 -0.0055 0.9999 0.5328
-3.750 -0.5171 0.04855 0.03958 0.0013 0.9999 0.5419
-3.500 -0.5015 0.04878 0.03979 0.0041 0.9999 0.5611
-3.250 -0.4856 0.04884 0.03983 0.0065 0.9999 0.5815
-3.000 -0.4690 0.04877 0.03973 0.0085 0.9999 0.6027
-2.750 -0.4579 0.04919 0.04017 0.0133 0.9999 0.6177
-2.500 -0.4450 0.04914 0.04012 0.0168 0.9999 0.6349
-2.250 -0.4301 0.04883 0.03978 0.0189 0.9999 0.6543
-2.000 -0.4140 0.04845 0.03938 0.0205 0.9999 0.6742
-1.750 -0.3963 0.04809 0.03899 0.0213 0.9999 0.6939
-1.500 -0.3884 0.04787 0.03880 0.0265 0.9999 0.7069
-1.250 -0.3738 0.04739 0.03832 0.0283 0.9999 0.7234
-1.000 -0.3563 0.04690 0.03781 0.0290 0.9999 0.7403
-0.750 -0.3413 0.04652 0.03742 0.0307 0.9999 0.7558
-0.500 -0.3289 0.04604 0.03696 0.0334 0.9999 0.7694
-0.250 -0.3116 0.04560 0.03652 0.0340 0.9999 0.7838
0.000 -0.2932 0.04529 0.03621 0.0342 0.9999 0.7980
0.250 -0.2797 0.04482 0.03578 0.0362 0.9999 0.8093
0.500 -0.2586 0.04459 0.03555 0.0354 0.9999 0.8213
0.750 -0.2428 0.04427 0.03526 0.0365 0.9999 0.8317
1.000 -0.2217 0.04414 0.03516 0.0356 0.9999 0.8414
1.250 -0.2033 0.04401 0.03507 0.0357 0.9999 0.8505
1.500 -0.1810 0.04408 0.03517 0.0343 0.9999 0.8588
1.750 -0.1632 0.04406 0.03522 0.0342 0.9999 0.8668
2.000 -0.1380 0.04446 0.03566 0.0319 0.9999 0.8743
2.250 -0.1207 0.04458 0.03586 0.0318 0.9999 0.8814
2.500 -0.0977 0.04511 0.03646 0.0299 0.9999 0.8887
2.750 -0.0771 0.04562 0.03706 0.0285 0.9999 0.8952
3.000 -0.0566 0.04629 0.03783 0.0270 0.9999 0.9022
3.250 0.0255 0.04872 0.04039 0.0150 0.9575 0.9107
3.500 0.1040 0.04930 0.04110 0.0061 0.9051 0.9189
3.750 0.1655 0.04880 0.04075 0.0008 0.8645 0.9269
4.000 0.2271 0.04792 0.04003 -0.0039 0.8291 0.9355
4.250 0.2959 0.04624 0.03854 -0.0085 0.7976 0.9438
4.500 0.3548 0.04403 0.03656 -0.0111 0.7642 0.9524
4.750 0.4125 0.04115 0.03392 -0.0126 0.7274 0.9619
5.000 0.4844 0.03645 0.02955 -0.0139 0.6824 0.9712
5.250 0.6173 0.02833 0.02063 -0.0175 0.5024 0.9779
5.500 0.6804 0.02993 0.02099 -0.0224 0.3929 0.9841
5.750 0.7731 0.03205 0.02242 -0.0337 0.3315 0.9890
6.000 0.8341 0.03372 0.02408 -0.0401 0.2981 0.9957
6.250 0.8766 0.03522 0.02550 -0.0433 0.2755 1.0001
6.500 0.8962 0.03647 0.02670 -0.0426 0.2611 1.0001
6.750 0.9203 0.03795 0.02800 -0.0427 0.2460 1.0001
7.000 0.9282 0.03905 0.02939 -0.0402 0.2342 1.0001
7.250 0.9511 0.04091 0.03130 -0.0404 0.2200 1.0001
7.500 0.9798 0.04306 0.03340 -0.0416 0.2056 1.0001
7.750 1.0042 0.04512 0.03559 -0.0421 0.1925 1.0001
8.000 1.0196 0.04777 0.03862 -0.0413 0.1819 1.0001
8.250 1.0480 0.05062 0.04144 -0.0428 0.1713 1.0001
8.500 1.0565 0.05346 0.04476 -0.0412 0.1635 1.0001
8.750 1.0807 0.05673 0.04807 -0.0423 0.1559 1.0001
9.000 1.0752 0.06034 0.05228 -0.0394 0.1519 1.0001
9.250 1.0800 0.06387 0.05612 -0.0382 0.1476 1.0001
9.500 1.1029 0.06765 0.05987 -0.0395 0.1424 1.0001
9.750 1.0810 0.07198 0.06469 -0.0359 0.1417 1.0001
10.000 1.0555 0.07647 0.06955 -0.0327 0.1415 1.0001
10.250 1.0278 0.08164 0.07504 -0.0305 0.1417 1.0001
10.500 0.9997 0.08747 0.08112 -0.0296 0.1423 1.0001
10.750 0.9739 0.09399 0.08783 -0.0300 0.1430 1.0001
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Polar data table (+)
Polar graphs
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