NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 50,000 Max Cl/Cd: 30.56 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k1-il-50000.txt Download as CSV file: xf-k1-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NYU/GRUMMAN K-1 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 -0.4552 0.11097 0.10324 -0.0120 1.0000 0.3154
-9.250 -0.6305 0.07559 0.06820 -0.0498 1.0000 0.1434
-9.000 -0.6466 0.07037 0.06301 -0.0515 1.0000 0.1409
-8.750 -0.7154 0.06177 0.05396 -0.0553 1.0000 0.1323
-8.500 -0.7205 0.05771 0.04969 -0.0547 1.0000 0.1317
-8.250 -0.7228 0.05366 0.04532 -0.0544 1.0000 0.1314
-8.000 -0.7204 0.04973 0.04096 -0.0541 1.0000 0.1316
-7.750 -0.7123 0.04601 0.03673 -0.0540 1.0000 0.1322
-7.500 -0.6983 0.04264 0.03289 -0.0538 1.0000 0.1331
-7.250 -0.6799 0.04000 0.03019 -0.0530 1.0000 0.1355
-7.000 -0.6609 0.03772 0.02771 -0.0523 1.0000 0.1401
-6.750 -0.6403 0.03528 0.02483 -0.0520 1.0000 0.1458
-6.500 -0.6190 0.03340 0.02297 -0.0511 1.0000 0.1529
-6.250 -0.5970 0.03153 0.02101 -0.0502 1.0000 0.1625
-6.000 -0.5750 0.02986 0.01937 -0.0492 1.0000 0.1768
-5.750 -0.5527 0.02823 0.01780 -0.0482 1.0000 0.1994
-5.500 -0.5311 0.02641 0.01637 -0.0473 1.0000 0.2399
-5.250 -0.5091 0.02431 0.01522 -0.0470 1.0000 0.3440
-5.000 -0.4937 0.02465 0.01635 -0.0428 1.0000 0.4481
-4.750 -0.4807 0.02604 0.01789 -0.0374 1.0000 0.5051
-4.500 -0.4702 0.02774 0.01963 -0.0310 1.0000 0.5447
-4.250 -0.4640 0.02965 0.02163 -0.0227 1.0000 0.5715
-4.000 -0.4511 0.03063 0.02250 -0.0178 1.0000 0.6057
-3.750 -0.4400 0.03128 0.02310 -0.0123 1.0000 0.6289
-3.500 -0.4281 0.03161 0.02333 -0.0074 1.0000 0.6520
-3.250 -0.4158 0.03172 0.02336 -0.0029 1.0000 0.6758
-3.000 -0.4030 0.03163 0.02318 0.0012 1.0000 0.7010
-2.750 -0.3873 0.03127 0.02270 0.0035 1.0000 0.7288
-2.500 -0.3757 0.03081 0.02217 0.0077 1.0000 0.7509
-2.250 -0.3622 0.03019 0.02145 0.0108 1.0000 0.7727
-2.000 -0.3470 0.02947 0.02063 0.0131 1.0000 0.7940
-1.750 -0.3307 0.02871 0.01978 0.0150 1.0000 0.8149
-1.500 -0.3137 0.02794 0.01892 0.0165 1.0000 0.8352
-1.250 -0.2964 0.02718 0.01807 0.0178 1.0000 0.8549
-1.000 -0.2796 0.02639 0.01721 0.0194 1.0000 0.8734
-0.750 -0.2610 0.02566 0.01641 0.0206 1.0000 0.8918
-0.500 -0.2399 0.02500 0.01569 0.0211 1.0000 0.9102
-0.250 -0.2144 0.02444 0.01509 0.0206 1.0000 0.9287
0.000 -0.1821 0.02406 0.01465 0.0186 1.0000 0.9473
0.250 -0.1403 0.02389 0.01443 0.0146 1.0000 0.9659
0.500 -0.0871 0.02395 0.01446 0.0081 1.0000 0.9830
0.750 -0.0376 0.02403 0.01454 0.0019 1.0000 0.9998
1.000 -0.0360 0.02364 0.01417 0.0040 1.0000 1.0000
1.250 -0.0243 0.02347 0.01401 0.0043 1.0000 1.0000
1.500 -0.0031 0.02353 0.01408 0.0030 1.0000 1.0000
1.750 0.0235 0.02378 0.01435 0.0007 1.0000 1.0000
2.000 0.0531 0.02416 0.01477 -0.0020 1.0000 1.0000
2.250 0.0839 0.02466 0.01531 -0.0050 1.0000 1.0000
2.500 0.1153 0.02526 0.01598 -0.0081 1.0000 1.0000
2.750 0.1465 0.02595 0.01675 -0.0111 1.0000 1.0000
3.000 0.1772 0.02674 0.01764 -0.0142 1.0000 1.0000
3.250 0.2070 0.02764 0.01866 -0.0171 1.0000 1.0000
3.500 0.2833 0.02945 0.02070 -0.0280 0.9731 1.0000
3.750 0.3714 0.03067 0.02223 -0.0390 0.9289 1.0000
4.000 0.4538 0.03067 0.02261 -0.0468 0.8862 1.0000
4.250 0.5154 0.02957 0.02189 -0.0498 0.8412 1.0000
4.500 0.5825 0.02660 0.01943 -0.0502 0.7821 1.0000
4.750 0.6428 0.02136 0.01431 -0.0443 0.6212 1.0000
5.000 0.6825 0.02233 0.01352 -0.0421 0.4455 1.0000
5.250 0.7153 0.02404 0.01475 -0.0428 0.3881 1.0000
5.500 0.7491 0.02560 0.01605 -0.0439 0.3468 1.0000
5.750 0.7811 0.02719 0.01750 -0.0447 0.3115 1.0000
6.000 0.8111 0.02891 0.01899 -0.0453 0.2775 1.0000
6.250 0.8392 0.03077 0.02074 -0.0456 0.2449 1.0000
6.500 0.8652 0.03290 0.02290 -0.0455 0.2135 1.0000
6.750 0.8907 0.03520 0.02510 -0.0455 0.1871 1.0000
7.000 0.9155 0.03773 0.02782 -0.0453 0.1677 1.0000
7.250 0.9397 0.04052 0.03080 -0.0450 0.1544 1.0000
7.500 0.9637 0.04340 0.03382 -0.0448 0.1449 1.0000
7.750 0.9814 0.04685 0.03782 -0.0438 0.1391 1.0000
8.000 1.0021 0.05007 0.04114 -0.0435 0.1334 1.0000
8.250 1.0093 0.05423 0.04598 -0.0419 0.1306 1.0000
8.500 1.0148 0.05878 0.05103 -0.0405 0.1295 1.0000
8.750 1.0149 0.06385 0.05656 -0.0392 0.1301 1.0000
9.000 1.0112 0.06916 0.06223 -0.0381 0.1315 1.0000
9.250 1.0060 0.07448 0.06782 -0.0373 0.1328 1.0000
9.500 1.0020 0.07980 0.07330 -0.0368 0.1339 1.0000
9.750 0.9377 0.08853 0.08243 -0.0378 0.1440 1.0000
10.000 0.9451 0.09411 0.08802 -0.0382 0.1464 1.0000
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