NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 100,000 Max Cl/Cd: 38.8 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k1-il-100000-n5.txt Download as CSV file: xf-k1-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7298 0.08226 0.07638 -0.0461 1.0000 0.0364
-12.250 -0.7573 0.07373 0.06768 -0.0527 1.0000 0.0362
-12.000 -0.7813 0.06680 0.06055 -0.0579 1.0000 0.0361
-11.750 -0.8015 0.06114 0.05467 -0.0617 1.0000 0.0360
-11.500 -0.8183 0.05647 0.04976 -0.0643 1.0000 0.0360
-11.250 -0.8321 0.05266 0.04571 -0.0657 1.0000 0.0360
-11.000 -0.8421 0.04937 0.04215 -0.0664 1.0000 0.0362
-10.750 -0.8469 0.04641 0.03887 -0.0661 1.0000 0.0364
-10.500 -0.8493 0.04383 0.03596 -0.0649 1.0000 0.0366
-10.250 -0.8434 0.04205 0.03408 -0.0633 1.0000 0.0370
-10.000 -0.8357 0.04055 0.03251 -0.0617 1.0000 0.0376
-9.750 -0.8281 0.03902 0.03083 -0.0601 1.0000 0.0384
-9.500 -0.8199 0.03737 0.02898 -0.0585 1.0000 0.0392
-9.250 -0.8099 0.03565 0.02698 -0.0569 1.0000 0.0401
-9.000 -0.7974 0.03400 0.02505 -0.0555 1.0000 0.0408
-8.750 -0.7823 0.03269 0.02371 -0.0541 1.0000 0.0414
-8.500 -0.7667 0.03145 0.02241 -0.0528 1.0000 0.0421
-8.250 -0.7504 0.03025 0.02112 -0.0516 1.0000 0.0430
-8.000 -0.7334 0.02910 0.01985 -0.0504 1.0000 0.0440
-7.750 -0.7156 0.02801 0.01862 -0.0492 1.0000 0.0452
-7.500 -0.6978 0.02700 0.01766 -0.0483 1.0000 0.0464
-7.250 -0.6789 0.02608 0.01669 -0.0475 1.0000 0.0483
-7.000 -0.6593 0.02517 0.01572 -0.0469 1.0000 0.0506
-6.750 -0.6300 0.02420 0.01472 -0.0482 0.9975 0.0538
-6.500 -0.5984 0.02321 0.01372 -0.0500 0.9945 0.0572
-6.250 -0.5654 0.02228 0.01275 -0.0521 0.9919 0.0623
-6.000 -0.5347 0.02141 0.01189 -0.0537 0.9888 0.0702
-5.750 -0.5038 0.02056 0.01112 -0.0553 0.9862 0.0830
-5.500 -0.4719 0.01969 0.01037 -0.0571 0.9840 0.1106
-5.250 -0.4390 0.01870 0.00970 -0.0594 0.9820 0.1610
-5.000 -0.4051 0.01781 0.00916 -0.0620 0.9804 0.2348
-4.750 -0.3723 0.01707 0.00883 -0.0641 0.9785 0.3175
-4.500 -0.3422 0.01668 0.00875 -0.0652 0.9757 0.3878
-4.250 -0.3115 0.01658 0.00884 -0.0660 0.9728 0.4458
-4.000 -0.2795 0.01665 0.00897 -0.0668 0.9699 0.4864
-3.750 -0.2465 0.01679 0.00911 -0.0678 0.9674 0.5127
-3.500 -0.2150 0.01691 0.00918 -0.0685 0.9645 0.5320
-3.250 -0.1873 0.01705 0.00927 -0.0684 0.9607 0.5502
-3.000 -0.1576 0.01725 0.00945 -0.0687 0.9575 0.5693
-2.750 -0.1260 0.01747 0.00962 -0.0694 0.9548 0.5870
-2.500 -0.0940 0.01769 0.00982 -0.0701 0.9525 0.5991
-2.250 -0.0661 0.01783 0.00992 -0.0702 0.9490 0.6100
-2.000 -0.0395 0.01800 0.01008 -0.0699 0.9450 0.6202
-1.750 -0.0092 0.01815 0.01020 -0.0705 0.9418 0.6303
-1.500 0.0223 0.01833 0.01038 -0.0711 0.9390 0.6395
-1.250 0.0579 0.01845 0.01046 -0.0728 0.9366 0.6495
-1.000 0.0800 0.01861 0.01066 -0.0716 0.9304 0.6565
-0.750 0.1113 0.01872 0.01074 -0.0725 0.9263 0.6659
-0.500 0.1436 0.01884 0.01090 -0.0733 0.9231 0.6727
-0.250 0.1777 0.01897 0.01107 -0.0745 0.9206 0.6797
0.000 0.2021 0.01910 0.01119 -0.0742 0.9146 0.6883
0.250 0.2301 0.01921 0.01139 -0.0742 0.9096 0.6937
0.500 0.2658 0.01924 0.01147 -0.0755 0.9051 0.7003
0.750 0.2965 0.01917 0.01142 -0.0759 0.8952 0.7082
1.000 0.3357 0.01869 0.01102 -0.0766 0.8824 0.7132
1.250 0.3693 0.01801 0.01039 -0.0760 0.8637 0.7192
1.500 0.4013 0.01741 0.00981 -0.0754 0.8456 0.7261
1.750 0.4288 0.01706 0.00955 -0.0745 0.8305 0.7317
2.000 0.4533 0.01692 0.00952 -0.0733 0.8164 0.7373
2.250 0.4812 0.01672 0.00940 -0.0728 0.8018 0.7438
2.500 0.5085 0.01649 0.00926 -0.0721 0.7832 0.7497
2.750 0.5337 0.01625 0.00913 -0.0708 0.7581 0.7551
3.000 0.5605 0.01600 0.00892 -0.0698 0.7210 0.7613
3.250 0.5932 0.01557 0.00829 -0.0691 0.6554 0.7674
3.500 0.6153 0.01591 0.00790 -0.0665 0.4962 0.7723
3.750 0.6326 0.01695 0.00824 -0.0646 0.3722 0.7783
4.000 0.6542 0.01782 0.00869 -0.0639 0.2993 0.7848
4.250 0.6757 0.01842 0.00911 -0.0627 0.2595 0.7900
4.500 0.6992 0.01896 0.00956 -0.0621 0.2327 0.7962
4.750 0.7239 0.01954 0.01003 -0.0617 0.2115 0.8029
5.000 0.7465 0.02004 0.01048 -0.0608 0.1935 0.8084
5.250 0.7702 0.02056 0.01096 -0.0603 0.1770 0.8150
5.500 0.7942 0.02108 0.01144 -0.0598 0.1610 0.8218
5.750 0.8174 0.02150 0.01187 -0.0591 0.1451 0.8285
6.000 0.8419 0.02192 0.01232 -0.0587 0.1279 0.8358
6.250 0.8645 0.02239 0.01280 -0.0579 0.1135 0.8430
6.500 0.8878 0.02288 0.01336 -0.0573 0.0974 0.8513
6.750 0.9098 0.02345 0.01394 -0.0563 0.0827 0.8598
7.000 0.9309 0.02417 0.01468 -0.0553 0.0705 0.8694
7.250 0.9505 0.02491 0.01540 -0.0540 0.0623 0.8805
7.500 0.9693 0.02571 0.01625 -0.0526 0.0564 0.8953
7.750 0.9866 0.02654 0.01716 -0.0509 0.0525 0.9208
8.000 1.0073 0.02757 0.01831 -0.0500 0.0493 1.0000
8.250 1.0298 0.02884 0.01960 -0.0498 0.0468 1.0000
8.500 1.0523 0.03012 0.02097 -0.0495 0.0442 1.0000
8.750 1.0740 0.03146 0.02239 -0.0490 0.0418 1.0000
9.000 1.0948 0.03278 0.02378 -0.0486 0.0397 1.0000
9.250 1.1150 0.03427 0.02539 -0.0479 0.0379 1.0000
9.500 1.1341 0.03575 0.02700 -0.0472 0.0362 1.0000
9.750 1.1521 0.03730 0.02858 -0.0464 0.0350 1.0000
10.000 1.1692 0.03931 0.03088 -0.0454 0.0339 1.0000
10.250 1.1844 0.04133 0.03313 -0.0442 0.0329 1.0000
10.500 1.1981 0.04331 0.03526 -0.0430 0.0322 1.0000
10.750 1.2113 0.04529 0.03732 -0.0419 0.0316 1.0000
11.000 1.2152 0.04806 0.04048 -0.0396 0.0310 1.0000
11.250 1.2135 0.05105 0.04386 -0.0371 0.0306 1.0000
11.500 1.2077 0.05417 0.04734 -0.0346 0.0301 1.0000
11.750 1.1989 0.05743 0.05091 -0.0325 0.0297 1.0000
12.000 1.1884 0.06086 0.05460 -0.0308 0.0293 1.0000
12.250 1.1764 0.06456 0.05854 -0.0297 0.0290 1.0000
12.500 1.1642 0.06846 0.06263 -0.0294 0.0287 1.0000
12.750 1.1488 0.07306 0.06744 -0.0299 0.0285 1.0000
13.000 1.1168 0.08058 0.07531 -0.0327 0.0286 1.0000
13.250 1.0372 0.10015 0.09547 -0.0465 0.0300 1.0000
13.500 0.9738 0.12314 0.11865 -0.0626 0.0313 1.0000
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