NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 200,000 Max Cl/Cd: 49.61 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k1-il-200000-n5.txt Download as CSV file: xf-k1-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8281 0.08067 0.07621 -0.0409 1.0000 0.0234
-13.500 -0.8692 0.06939 0.06461 -0.0494 1.0000 0.0232
-13.250 -0.8901 0.06258 0.05756 -0.0543 1.0000 0.0232
-13.000 -0.9034 0.05736 0.05214 -0.0578 1.0000 0.0233
-12.750 -0.9122 0.05304 0.04762 -0.0604 1.0000 0.0234
-12.500 -0.9176 0.04932 0.04371 -0.0625 1.0000 0.0235
-12.250 -0.9204 0.04605 0.04025 -0.0641 1.0000 0.0237
-12.000 -0.9209 0.04315 0.03715 -0.0653 1.0000 0.0239
-11.750 -0.9197 0.04057 0.03438 -0.0660 1.0000 0.0242
-11.500 -0.9177 0.03834 0.03195 -0.0663 1.0000 0.0245
-11.250 -0.9126 0.03627 0.02966 -0.0665 1.0000 0.0249
-11.000 -0.9091 0.03455 0.02769 -0.0653 1.0000 0.0254
-10.750 -0.9065 0.03315 0.02609 -0.0631 1.0000 0.0257
-10.500 -0.8991 0.03208 0.02499 -0.0611 1.0000 0.0260
-10.250 -0.8888 0.03101 0.02386 -0.0596 0.9996 0.0264
-10.000 -0.8631 0.02962 0.02236 -0.0609 0.9964 0.0269
-9.750 -0.8364 0.02827 0.02088 -0.0622 0.9937 0.0274
-9.500 -0.8095 0.02699 0.01947 -0.0634 0.9914 0.0279
-9.250 -0.7839 0.02583 0.01817 -0.0642 0.9884 0.0285
-9.000 -0.7568 0.02475 0.01699 -0.0652 0.9857 0.0293
-8.750 -0.7284 0.02379 0.01603 -0.0666 0.9834 0.0301
-8.500 -0.6983 0.02286 0.01505 -0.0682 0.9814 0.0310
-8.250 -0.6672 0.02192 0.01402 -0.0699 0.9796 0.0319
-8.000 -0.6404 0.02107 0.01309 -0.0706 0.9759 0.0328
-7.750 -0.6118 0.02023 0.01226 -0.0719 0.9725 0.0337
-7.500 -0.5815 0.01947 0.01145 -0.0733 0.9699 0.0350
-7.250 -0.5505 0.01877 0.01067 -0.0748 0.9678 0.0367
-6.750 -0.4925 0.01752 0.00935 -0.0768 0.9623 0.0410
-6.500 -0.4639 0.01697 0.00878 -0.0776 0.9590 0.0447
-6.250 -0.4335 0.01640 0.00818 -0.0788 0.9562 0.0501
-6.000 -0.4023 0.01578 0.00758 -0.0802 0.9538 0.0584
-5.750 -0.3706 0.01513 0.00706 -0.0817 0.9519 0.0762
-5.500 -0.3441 0.01457 0.00665 -0.0821 0.9482 0.1102
-5.250 -0.3160 0.01400 0.00626 -0.0829 0.9447 0.1473
-5.000 -0.2864 0.01343 0.00591 -0.0840 0.9420 0.1971
-4.750 -0.2558 0.01288 0.00560 -0.0852 0.9398 0.2545
-4.500 -0.2248 0.01231 0.00535 -0.0865 0.9378 0.3274
-4.250 -0.1948 0.01193 0.00524 -0.0874 0.9354 0.3914
-4.000 -0.1679 0.01178 0.00521 -0.0874 0.9314 0.4313
-3.750 -0.1392 0.01169 0.00518 -0.0876 0.9280 0.4641
-3.500 -0.1098 0.01164 0.00518 -0.0879 0.9253 0.4878
-3.250 -0.0797 0.01161 0.00516 -0.0883 0.9230 0.5061
-3.000 -0.0495 0.01160 0.00513 -0.0886 0.9210 0.5219
-2.750 -0.0216 0.01164 0.00521 -0.0886 0.9179 0.5386
-2.500 0.0056 0.01170 0.00530 -0.0884 0.9141 0.5547
-2.250 0.0341 0.01174 0.00535 -0.0884 0.9108 0.5682
-2.000 0.0632 0.01178 0.00540 -0.0886 0.9080 0.5788
-1.750 0.0929 0.01180 0.00541 -0.0888 0.9057 0.5882
-1.500 0.1224 0.01184 0.00548 -0.0889 0.9036 0.5971
-1.250 0.1504 0.01191 0.00554 -0.0890 0.9000 0.6066
-1.000 0.1773 0.01200 0.00569 -0.0887 0.8959 0.6136
-0.750 0.2059 0.01204 0.00574 -0.0887 0.8921 0.6219
-0.500 0.2354 0.01195 0.00566 -0.0886 0.8875 0.6290
-0.250 0.2617 0.01187 0.00562 -0.0878 0.8791 0.6350
0.000 0.2894 0.01163 0.00538 -0.0869 0.8692 0.6418
0.250 0.3156 0.01140 0.00513 -0.0859 0.8549 0.6483
0.500 0.3417 0.01119 0.00495 -0.0848 0.8407 0.6532
0.750 0.3693 0.01102 0.00478 -0.0841 0.8288 0.6588
1.000 0.3966 0.01095 0.00472 -0.0836 0.8131 0.6651
1.250 0.4241 0.01087 0.00467 -0.0831 0.7975 0.6703
1.500 0.4512 0.01081 0.00466 -0.0825 0.7802 0.6748
1.750 0.4787 0.01077 0.00462 -0.0820 0.7586 0.6801
2.000 0.5064 0.01074 0.00454 -0.0815 0.7271 0.6859
2.250 0.5325 0.01079 0.00437 -0.0804 0.6755 0.6906
2.500 0.5548 0.01122 0.00437 -0.0788 0.5685 0.6948
2.750 0.5728 0.01223 0.00469 -0.0770 0.4315 0.6996
3.000 0.5940 0.01308 0.00507 -0.0761 0.3362 0.7048
3.250 0.6177 0.01371 0.00542 -0.0755 0.2745 0.7098
3.500 0.6418 0.01419 0.00576 -0.0750 0.2354 0.7138
4.000 0.6918 0.01509 0.00643 -0.0741 0.1856 0.7233
4.250 0.7176 0.01552 0.00676 -0.0739 0.1666 0.7286
4.500 0.7425 0.01587 0.00708 -0.0734 0.1510 0.7325
4.750 0.7679 0.01621 0.00740 -0.0730 0.1378 0.7368
5.000 0.7935 0.01655 0.00773 -0.0727 0.1262 0.7418
5.250 0.8195 0.01691 0.00807 -0.0725 0.1161 0.7471
5.500 0.8445 0.01725 0.00844 -0.0720 0.1056 0.7512
5.750 0.8697 0.01758 0.00880 -0.0715 0.0917 0.7555
6.000 0.8944 0.01803 0.00920 -0.0711 0.0749 0.7605
6.250 0.9186 0.01863 0.00968 -0.0706 0.0577 0.7658
6.500 0.9415 0.01928 0.01030 -0.0699 0.0483 0.7701
6.750 0.9644 0.01994 0.01099 -0.0691 0.0428 0.7748
7.000 0.9876 0.02062 0.01169 -0.0684 0.0392 0.7799
7.250 1.0108 0.02129 0.01241 -0.0678 0.0361 0.7853
7.500 1.0328 0.02195 0.01315 -0.0669 0.0337 0.7902
7.750 1.0546 0.02267 0.01391 -0.0661 0.0316 0.7958
8.000 1.0768 0.02339 0.01473 -0.0653 0.0299 0.8015
8.250 1.0975 0.02414 0.01557 -0.0643 0.0287 0.8069
8.500 1.1175 0.02498 0.01648 -0.0632 0.0278 0.8134
9.000 1.1568 0.02670 0.01844 -0.0609 0.0259 0.8269
9.250 1.1752 0.02763 0.01944 -0.0597 0.0251 0.8347
9.500 1.1923 0.02865 0.02056 -0.0582 0.0245 0.8436
10.000 1.2242 0.03076 0.02302 -0.0549 0.0232 0.8710
10.250 1.2343 0.03162 0.02408 -0.0520 0.0227 0.9166
10.500 1.2484 0.03273 0.02526 -0.0505 0.0222 1.0000
10.750 1.2619 0.03405 0.02662 -0.0490 0.0216 1.0000
11.000 1.2742 0.03548 0.02828 -0.0473 0.0208 1.0000
11.250 1.2849 0.03687 0.02982 -0.0456 0.0201 1.0000
11.500 1.2944 0.03828 0.03133 -0.0439 0.0195 1.0000
11.750 1.3028 0.03976 0.03286 -0.0422 0.0191 1.0000
12.000 1.3088 0.04158 0.03480 -0.0404 0.0187 1.0000
12.250 1.3111 0.04375 0.03725 -0.0384 0.0182 1.0000
12.500 1.3120 0.04606 0.03979 -0.0366 0.0178 1.0000
12.750 1.3112 0.04858 0.04251 -0.0350 0.0175 1.0000
13.000 1.3087 0.05130 0.04543 -0.0336 0.0172 1.0000
13.250 1.3045 0.05427 0.04859 -0.0326 0.0170 1.0000
13.500 1.2987 0.05756 0.05206 -0.0320 0.0168 1.0000
13.750 1.2911 0.06119 0.05587 -0.0318 0.0167 1.0000
14.000 1.2819 0.06528 0.06013 -0.0322 0.0165 1.0000
14.250 1.2704 0.06997 0.06500 -0.0334 0.0164 1.0000
14.500 1.2561 0.07548 0.07070 -0.0355 0.0164 1.0000
14.750 1.2394 0.08190 0.07732 -0.0386 0.0163 1.0000
15.000 1.2169 0.09030 0.08597 -0.0438 0.0163 1.0000
15.250 1.1830 0.10248 0.09847 -0.0522 0.0164 1.0000
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