NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 200,000 Max Cl/Cd: 53.76 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k1-il-200000.txt Download as CSV file: xf-k1-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4541 0.10116 0.09751 -0.0358 1.0000 0.0954
-10.750 -0.7775 0.06012 0.05578 -0.0655 1.0000 0.0597
-10.500 -0.8265 0.04971 0.04481 -0.0658 1.0000 0.0482
-10.250 -0.8756 0.04396 0.03813 -0.0615 1.0000 0.0449
-10.000 -0.8717 0.04133 0.03532 -0.0596 1.0000 0.0447
-9.750 -0.8666 0.03874 0.03247 -0.0579 1.0000 0.0445
-9.500 -0.8593 0.03627 0.02966 -0.0565 1.0000 0.0446
-9.250 -0.8492 0.03411 0.02707 -0.0552 1.0000 0.0449
-9.000 -0.8343 0.03201 0.02474 -0.0543 1.0000 0.0455
-8.750 -0.8160 0.03037 0.02309 -0.0533 1.0000 0.0460
-8.500 -0.7974 0.02878 0.02133 -0.0525 1.0000 0.0463
-8.250 -0.7778 0.02734 0.01976 -0.0516 1.0000 0.0468
-8.000 -0.7573 0.02605 0.01833 -0.0509 1.0000 0.0473
-7.750 -0.7361 0.02489 0.01703 -0.0502 1.0000 0.0482
-7.500 -0.7141 0.02392 0.01585 -0.0496 1.0000 0.0494
-7.250 -0.6920 0.02279 0.01473 -0.0490 1.0000 0.0506
-7.000 -0.6693 0.02185 0.01381 -0.0485 1.0000 0.0518
-6.750 -0.6458 0.02099 0.01294 -0.0481 1.0000 0.0532
-6.250 -0.5971 0.01927 0.01126 -0.0479 1.0000 0.0570
-6.000 -0.5715 0.01858 0.01053 -0.0481 1.0000 0.0601
-5.750 -0.5443 0.01771 0.00976 -0.0489 1.0000 0.0644
-5.500 -0.5088 0.01687 0.00898 -0.0514 0.9983 0.0731
-5.250 -0.4722 0.01598 0.00827 -0.0541 0.9968 0.0953
-5.000 -0.4325 0.01434 0.00735 -0.0584 0.9960 0.2083
-4.750 -0.3943 0.01350 0.00699 -0.0617 0.9948 0.3142
-4.500 -0.3569 0.01312 0.00694 -0.0643 0.9934 0.3943
-4.250 -0.3207 0.01305 0.00704 -0.0664 0.9917 0.4514
-4.000 -0.2892 0.01312 0.00721 -0.0673 0.9889 0.4952
-3.750 -0.2570 0.01332 0.00747 -0.0682 0.9860 0.5292
-3.500 -0.2235 0.01357 0.00775 -0.0693 0.9833 0.5527
-3.250 -0.1887 0.01388 0.00804 -0.0707 0.9810 0.5723
-3.000 -0.1547 0.01416 0.00830 -0.0719 0.9786 0.5884
-2.750 -0.1275 0.01438 0.00853 -0.0718 0.9747 0.6005
-2.500 -0.0962 0.01462 0.00876 -0.0725 0.9714 0.6118
-2.250 -0.0605 0.01494 0.00904 -0.0741 0.9683 0.6268
-2.000 -0.0271 0.01532 0.00951 -0.0748 0.9651 0.6366
-1.750 0.0000 0.01552 0.00965 -0.0748 0.9599 0.6481
-1.500 0.0309 0.01575 0.00995 -0.0752 0.9560 0.6548
-1.250 0.0662 0.01599 0.01018 -0.0768 0.9533 0.6643
-1.000 0.0974 0.01621 0.01042 -0.0775 0.9499 0.6720
-0.750 0.1217 0.01643 0.01068 -0.0767 0.9441 0.6790
-0.500 0.1586 0.01657 0.01079 -0.0787 0.9400 0.6889
-0.250 0.1984 0.01661 0.01092 -0.0804 0.9348 0.6944
0.000 0.2362 0.01644 0.01078 -0.0816 0.9242 0.7015
0.250 0.2847 0.01595 0.01029 -0.0845 0.9123 0.7097
0.500 0.3289 0.01534 0.00974 -0.0859 0.9039 0.7147
0.750 0.3540 0.01519 0.00965 -0.0848 0.8931 0.7209
1.000 0.3903 0.01480 0.00925 -0.0856 0.8869 0.7286
1.250 0.4143 0.01460 0.00915 -0.0841 0.8769 0.7332
1.500 0.4441 0.01419 0.00881 -0.0834 0.8693 0.7390
1.750 0.4718 0.01394 0.00860 -0.0828 0.8588 0.7461
2.000 0.5002 0.01347 0.00820 -0.0818 0.8498 0.7511
2.250 0.5250 0.01318 0.00799 -0.0804 0.8363 0.7566
2.500 0.5526 0.01280 0.00767 -0.0795 0.8216 0.7632
2.750 0.5793 0.01241 0.00733 -0.0783 0.8020 0.7687
3.000 0.6044 0.01206 0.00703 -0.0768 0.7748 0.7739
3.250 0.6302 0.01179 0.00672 -0.0754 0.7249 0.7803
3.500 0.6505 0.01210 0.00625 -0.0726 0.5595 0.7859
3.750 0.6578 0.01387 0.00679 -0.0691 0.3442 0.7909
4.000 0.6768 0.01488 0.00729 -0.0679 0.2649 0.7971
4.250 0.7010 0.01551 0.00770 -0.0676 0.2296 0.8033
4.500 0.7234 0.01597 0.00804 -0.0667 0.2079 0.8084
4.750 0.7477 0.01641 0.00841 -0.0662 0.1909 0.8147
5.000 0.7735 0.01681 0.00876 -0.0660 0.1766 0.8212
5.250 0.7975 0.01711 0.00911 -0.0653 0.1643 0.8267
5.500 0.8225 0.01746 0.00948 -0.0649 0.1520 0.8333
5.750 0.8475 0.01778 0.00979 -0.0646 0.1381 0.8399
6.000 0.8710 0.01808 0.01010 -0.0639 0.1209 0.8466
6.250 0.8954 0.01857 0.01050 -0.0635 0.0950 0.8536
6.500 0.9166 0.01928 0.01108 -0.0624 0.0744 0.8603
6.750 0.9385 0.02004 0.01181 -0.0613 0.0646 0.8685
7.000 0.9595 0.02079 0.01256 -0.0602 0.0590 0.8765
7.250 0.9805 0.02159 0.01336 -0.0592 0.0545 0.8855
7.500 1.0002 0.02244 0.01420 -0.0579 0.0512 0.8953
7.750 1.0202 0.02324 0.01505 -0.0565 0.0485 0.9079
8.000 1.0383 0.02416 0.01602 -0.0547 0.0466 0.9270
8.250 1.0599 0.02505 0.01703 -0.0537 0.0447 1.0000
8.500 1.0881 0.02656 0.01840 -0.0543 0.0431 1.0000
8.750 1.1152 0.02797 0.02004 -0.0545 0.0416 1.0000
9.000 1.1423 0.02950 0.02165 -0.0547 0.0402 1.0000
9.250 1.1701 0.03133 0.02341 -0.0552 0.0391 1.0000
9.500 1.1908 0.03320 0.02567 -0.0544 0.0379 1.0000
9.750 1.2113 0.03487 0.02755 -0.0537 0.0365 1.0000
10.000 1.2365 0.03665 0.02921 -0.0540 0.0353 1.0000
10.250 1.2467 0.03900 0.03210 -0.0519 0.0343 1.0000
10.500 1.2566 0.04135 0.03484 -0.0500 0.0333 1.0000
10.750 1.2692 0.04347 0.03714 -0.0486 0.0324 1.0000
11.000 1.2881 0.04556 0.03920 -0.0481 0.0318 1.0000
11.250 1.2920 0.04885 0.04277 -0.0459 0.0314 1.0000
11.500 1.2829 0.05229 0.04667 -0.0425 0.0313 1.0000
11.750 1.2678 0.05567 0.05041 -0.0386 0.0312 1.0000
12.000 1.2499 0.05923 0.05428 -0.0352 0.0313 1.0000
12.250 1.2305 0.06313 0.05844 -0.0326 0.0313 1.0000
12.500 1.2098 0.06747 0.06302 -0.0310 0.0313 1.0000
12.750 1.1909 0.07211 0.06787 -0.0304 0.0314 1.0000
13.000 1.1735 0.07710 0.07301 -0.0307 0.0315 1.0000
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Polar data table (+)
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