NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 50,000 Max Cl/Cd: 29.09 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k1-il-50000-n5.txt Download as CSV file: xf-k1-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6666 0.08196 0.07389 -0.0506 1.0000 0.0601
-11.000 -0.6904 0.07479 0.06663 -0.0556 1.0000 0.0597
-10.750 -0.7135 0.06881 0.06052 -0.0594 1.0000 0.0594
-10.500 -0.7347 0.06406 0.05561 -0.0615 1.0000 0.0592
-10.250 -0.7518 0.06000 0.05135 -0.0627 1.0000 0.0592
-10.000 -0.7627 0.05634 0.04742 -0.0628 1.0000 0.0594
-9.750 -0.7690 0.05305 0.04380 -0.0620 1.0000 0.0597
-9.500 -0.7715 0.05003 0.04043 -0.0609 1.0000 0.0602
-9.250 -0.7620 0.04814 0.03851 -0.0596 1.0000 0.0614
-9.000 -0.7543 0.04609 0.03629 -0.0583 1.0000 0.0630
-8.750 -0.7463 0.04384 0.03374 -0.0570 1.0000 0.0646
-8.500 -0.7354 0.04168 0.03128 -0.0556 1.0000 0.0663
-8.250 -0.7208 0.04008 0.02962 -0.0542 1.0000 0.0680
-8.000 -0.7055 0.03842 0.02779 -0.0528 1.0000 0.0698
-7.750 -0.6895 0.03683 0.02598 -0.0513 1.0000 0.0724
-7.500 -0.6735 0.03563 0.02479 -0.0499 1.0000 0.0755
-7.250 -0.6566 0.03437 0.02337 -0.0483 1.0000 0.0793
-7.000 -0.6399 0.03325 0.02224 -0.0468 1.0000 0.0832
-6.750 -0.6230 0.03213 0.02107 -0.0454 1.0000 0.0882
-6.500 -0.6059 0.03103 0.01990 -0.0441 1.0000 0.0951
-6.250 -0.5885 0.02988 0.01875 -0.0431 1.0000 0.1038
-6.000 -0.5706 0.02863 0.01757 -0.0425 1.0000 0.1162
-5.750 -0.5515 0.02725 0.01633 -0.0423 1.0000 0.1363
-5.500 -0.5304 0.02568 0.01505 -0.0429 1.0000 0.1735
-5.250 -0.5072 0.02409 0.01395 -0.0441 1.0000 0.2409
-5.000 -0.4838 0.02305 0.01340 -0.0447 1.0000 0.3233
-4.750 -0.4620 0.02271 0.01341 -0.0439 1.0000 0.3948
-4.500 -0.4415 0.02290 0.01379 -0.0422 1.0000 0.4563
-4.250 -0.4208 0.02325 0.01415 -0.0404 1.0000 0.4989
-4.000 -0.3992 0.02350 0.01432 -0.0389 1.0000 0.5269
-3.750 -0.3784 0.02380 0.01451 -0.0371 1.0000 0.5496
-3.500 -0.3580 0.02412 0.01476 -0.0352 1.0000 0.5714
-3.250 -0.3376 0.02444 0.01499 -0.0334 1.0000 0.5917
-3.000 -0.3166 0.02467 0.01513 -0.0319 1.0000 0.6105
-2.750 -0.2939 0.02479 0.01511 -0.0310 1.0000 0.6280
-2.500 -0.2741 0.02495 0.01521 -0.0292 1.0000 0.6413
-2.250 -0.2524 0.02502 0.01521 -0.0281 1.0000 0.6549
-2.000 -0.2279 0.02504 0.01511 -0.0280 1.0000 0.6699
-1.750 -0.2076 0.02510 0.01513 -0.0265 1.0000 0.6816
-1.500 -0.1844 0.02511 0.01507 -0.0261 1.0000 0.6941
-1.250 -0.1596 0.02513 0.01500 -0.0261 1.0000 0.7072
-1.000 -0.1386 0.02514 0.01500 -0.0251 1.0000 0.7173
-0.750 -0.1052 0.02524 0.01502 -0.0269 0.9962 0.7298
-0.500 -0.0740 0.02538 0.01514 -0.0278 0.9922 0.7398
-0.250 -0.0420 0.02548 0.01520 -0.0294 0.9876 0.7505
0.000 -0.0103 0.02562 0.01533 -0.0306 0.9829 0.7604
0.250 0.0244 0.02581 0.01551 -0.0326 0.9785 0.7703
0.500 0.0550 0.02594 0.01566 -0.0337 0.9725 0.7799
0.750 0.0906 0.02615 0.01591 -0.0358 0.9670 0.7892
1.000 0.1215 0.02632 0.01612 -0.0370 0.9601 0.7986
1.250 0.1571 0.02654 0.01640 -0.0390 0.9533 0.8075
1.500 0.1885 0.02672 0.01666 -0.0403 0.9449 0.8169
1.750 0.2257 0.02694 0.01699 -0.0424 0.9372 0.8255
2.000 0.2575 0.02706 0.01722 -0.0435 0.9253 0.8349
2.250 0.2970 0.02699 0.01729 -0.0453 0.9081 0.8433
2.500 0.3454 0.02650 0.01696 -0.0476 0.8832 0.8521
2.750 0.3811 0.02583 0.01644 -0.0475 0.8563 0.8606
3.000 0.4180 0.02522 0.01600 -0.0478 0.8345 0.8699
3.250 0.4495 0.02455 0.01554 -0.0471 0.8132 0.8793
3.500 0.4815 0.02379 0.01497 -0.0463 0.7903 0.8897
3.750 0.5016 0.02329 0.01467 -0.0439 0.7608 0.9013
4.000 0.5248 0.02269 0.01430 -0.0419 0.7255 0.9145
4.250 0.5554 0.02182 0.01362 -0.0405 0.6764 0.9292
4.500 0.5963 0.02080 0.01234 -0.0395 0.5485 0.9443
4.750 0.6252 0.02149 0.01194 -0.0382 0.4001 0.9694
5.000 0.6461 0.02266 0.01263 -0.0378 0.3319 1.0000
5.250 0.6712 0.02381 0.01349 -0.0381 0.2925 1.0000
5.500 0.6985 0.02489 0.01440 -0.0387 0.2647 1.0000
5.750 0.7270 0.02594 0.01533 -0.0395 0.2408 1.0000
6.000 0.7561 0.02694 0.01629 -0.0402 0.2175 1.0000
6.250 0.7843 0.02795 0.01725 -0.0409 0.1948 1.0000
6.500 0.8119 0.02903 0.01822 -0.0415 0.1737 1.0000
6.750 0.8398 0.03013 0.01942 -0.0420 0.1526 1.0000
7.000 0.8649 0.03127 0.02049 -0.0422 0.1334 1.0000
7.250 0.8893 0.03242 0.02169 -0.0423 0.1153 1.0000
7.500 0.9148 0.03380 0.02311 -0.0423 0.1012 1.0000
7.750 0.9403 0.03527 0.02467 -0.0423 0.0904 1.0000
8.000 0.9647 0.03678 0.02624 -0.0422 0.0825 1.0000
8.250 0.9897 0.03864 0.02825 -0.0421 0.0766 1.0000
8.500 1.0129 0.04059 0.03037 -0.0418 0.0718 1.0000
8.750 1.0338 0.04230 0.03212 -0.0414 0.0678 1.0000
9.000 1.0534 0.04478 0.03499 -0.0408 0.0641 1.0000
9.250 1.0723 0.04702 0.03734 -0.0402 0.0621 1.0000
9.500 1.0848 0.05047 0.04131 -0.0390 0.0601 1.0000
9.750 1.0967 0.05310 0.04416 -0.0379 0.0581 1.0000
10.000 1.1040 0.05604 0.04739 -0.0365 0.0564 1.0000
10.250 1.1000 0.06008 0.05192 -0.0345 0.0550 1.0000
10.500 1.0947 0.06375 0.05592 -0.0327 0.0539 1.0000
10.750 1.0852 0.06732 0.05975 -0.0308 0.0533 1.0000
11.000 1.0712 0.07136 0.06404 -0.0293 0.0529 1.0000
11.250 1.0488 0.07640 0.06935 -0.0287 0.0528 1.0000
11.500 1.0070 0.08443 0.07772 -0.0307 0.0535 1.0000
11.750 0.9570 0.09597 0.08952 -0.0374 0.0547 1.0000
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Polar data table (+)
Polar graphs
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