NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 500,000 Max Cl/Cd: 73.92 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k1-il-500000.txt Download as CSV file: xf-k1-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9643 0.06225 0.05865 -0.0544 1.0000 0.0226
-13.750 -0.9828 0.05666 0.05284 -0.0583 1.0000 0.0225
-13.500 -0.9969 0.05186 0.04785 -0.0612 1.0000 0.0226
-13.250 -1.0057 0.04773 0.04354 -0.0632 1.0000 0.0226
-13.000 -1.0082 0.04437 0.04005 -0.0646 1.0000 0.0228
-12.750 -1.0061 0.04162 0.03719 -0.0658 1.0000 0.0229
-12.500 -0.9988 0.03950 0.03499 -0.0666 1.0000 0.0231
-12.250 -0.9912 0.03751 0.03292 -0.0675 1.0000 0.0234
-12.000 -0.9823 0.03546 0.03073 -0.0686 1.0000 0.0236
-11.750 -0.9748 0.03363 0.02875 -0.0685 1.0000 0.0239
-11.500 -0.9764 0.03230 0.02728 -0.0658 1.0000 0.0241
-11.250 -0.9781 0.03107 0.02592 -0.0626 1.0000 0.0243
-11.000 -0.9591 0.02936 0.02399 -0.0634 0.9983 0.0247
-10.750 -0.9327 0.02768 0.02204 -0.0653 0.9959 0.0253
-10.500 -0.9042 0.02621 0.02030 -0.0673 0.9939 0.0257
-10.250 -0.8766 0.02441 0.01848 -0.0685 0.9928 0.0261
-10.000 -0.8477 0.02327 0.01731 -0.0698 0.9913 0.0266
-9.750 -0.8199 0.02227 0.01626 -0.0708 0.9890 0.0270
-9.500 -0.7907 0.02131 0.01523 -0.0720 0.9869 0.0275
-9.250 -0.7603 0.02039 0.01424 -0.0734 0.9852 0.0281
-9.000 -0.7284 0.01958 0.01333 -0.0750 0.9837 0.0287
-8.750 -0.6961 0.01869 0.01236 -0.0767 0.9824 0.0293
-8.500 -0.6643 0.01766 0.01136 -0.0785 0.9810 0.0298
-8.250 -0.6314 0.01690 0.01059 -0.0804 0.9795 0.0304
-8.000 -0.6049 0.01628 0.00995 -0.0808 0.9759 0.0311
-7.750 -0.5759 0.01567 0.00930 -0.0817 0.9730 0.0319
-7.500 -0.5455 0.01515 0.00872 -0.0827 0.9706 0.0328
-7.250 -0.5153 0.01441 0.00801 -0.0841 0.9684 0.0340
-7.000 -0.4845 0.01392 0.00749 -0.0852 0.9665 0.0354
-6.750 -0.4576 0.01346 0.00700 -0.0855 0.9632 0.0370
-6.500 -0.4304 0.01300 0.00655 -0.0858 0.9595 0.0392
-6.250 -0.4021 0.01256 0.00610 -0.0862 0.9563 0.0424
-6.000 -0.3733 0.01212 0.00568 -0.0867 0.9537 0.0482
-5.750 -0.3450 0.01158 0.00520 -0.0873 0.9511 0.0617
-5.500 -0.3177 0.01087 0.00477 -0.0879 0.9477 0.1115
-5.250 -0.2896 0.01033 0.00445 -0.0886 0.9446 0.1572
-5.000 -0.2612 0.00982 0.00418 -0.0892 0.9419 0.2108
-4.750 -0.2326 0.00937 0.00394 -0.0898 0.9395 0.2658
-4.500 -0.2039 0.00898 0.00376 -0.0903 0.9373 0.3227
-4.250 -0.1750 0.00867 0.00365 -0.0909 0.9349 0.3765
-4.000 -0.1459 0.00844 0.00357 -0.0914 0.9318 0.4230
-3.750 -0.1170 0.00829 0.00354 -0.0917 0.9289 0.4623
-3.500 -0.0883 0.00820 0.00353 -0.0918 0.9262 0.4909
-3.250 -0.0598 0.00816 0.00352 -0.0918 0.9238 0.5110
-3.000 -0.0313 0.00815 0.00351 -0.0918 0.9217 0.5273
-2.750 -0.0027 0.00818 0.00355 -0.0918 0.9194 0.5418
-2.500 0.0264 0.00817 0.00358 -0.0921 0.9162 0.5536
-2.250 0.0553 0.00819 0.00358 -0.0922 0.9127 0.5649
-2.000 0.0833 0.00816 0.00360 -0.0920 0.9093 0.5759
-1.750 0.1110 0.00813 0.00354 -0.0916 0.9059 0.5862
-1.500 0.1379 0.00809 0.00354 -0.0910 0.9017 0.5952
-1.250 0.1655 0.00802 0.00346 -0.0906 0.8947 0.6044
-1.000 0.1917 0.00786 0.00331 -0.0897 0.8884 0.6119
-0.750 0.2184 0.00775 0.00321 -0.0889 0.8809 0.6192
-0.500 0.2455 0.00763 0.00304 -0.0883 0.8717 0.6264
-0.250 0.2724 0.00750 0.00295 -0.0876 0.8643 0.6329
0.000 0.3004 0.00744 0.00291 -0.0872 0.8553 0.6394
0.500 0.3567 0.00734 0.00282 -0.0867 0.8387 0.6515
0.750 0.3848 0.00731 0.00280 -0.0864 0.8307 0.6568
1.000 0.4134 0.00730 0.00282 -0.0863 0.8210 0.6625
1.250 0.4418 0.00730 0.00276 -0.0860 0.8097 0.6678
1.500 0.4700 0.00726 0.00278 -0.0858 0.7948 0.6725
1.750 0.4979 0.00726 0.00280 -0.0855 0.7775 0.6773
2.000 0.5256 0.00731 0.00279 -0.0851 0.7526 0.6824
2.250 0.5522 0.00747 0.00277 -0.0845 0.6994 0.6874
2.500 0.5743 0.00809 0.00286 -0.0832 0.5797 0.6917
2.750 0.5920 0.00943 0.00335 -0.0817 0.3916 0.6958
3.000 0.6143 0.01035 0.00373 -0.0810 0.2777 0.7004
3.250 0.6392 0.01094 0.00402 -0.0806 0.2166 0.7052
3.500 0.6655 0.01135 0.00427 -0.0805 0.1871 0.7095
3.750 0.6919 0.01163 0.00450 -0.0802 0.1704 0.7137
4.000 0.7185 0.01191 0.00475 -0.0799 0.1577 0.7179
4.250 0.7452 0.01219 0.00499 -0.0798 0.1465 0.7225
4.500 0.7725 0.01243 0.00520 -0.0796 0.1369 0.7271
4.750 0.7993 0.01265 0.00542 -0.0794 0.1276 0.7312
5.000 0.8258 0.01289 0.00566 -0.0792 0.1179 0.7352
5.250 0.8523 0.01316 0.00591 -0.0789 0.1069 0.7396
5.500 0.8788 0.01344 0.00614 -0.0787 0.0907 0.7443
5.750 0.9034 0.01401 0.00650 -0.0783 0.0589 0.7485
6.000 0.9266 0.01469 0.00707 -0.0775 0.0433 0.7524
6.250 0.9512 0.01522 0.00759 -0.0770 0.0380 0.7566
6.500 0.9754 0.01579 0.00816 -0.0764 0.0351 0.7614
6.750 1.0005 0.01628 0.00867 -0.0759 0.0331 0.7659
7.000 1.0236 0.01692 0.00932 -0.0751 0.0315 0.7699
7.250 1.0479 0.01738 0.00987 -0.0745 0.0302 0.7742
7.500 1.0715 0.01794 0.01047 -0.0738 0.0290 0.7792
7.750 1.0934 0.01874 0.01126 -0.0730 0.0279 0.7840
8.000 1.1169 0.01926 0.01188 -0.0722 0.0270 0.7884
8.250 1.1398 0.01984 0.01252 -0.0714 0.0259 0.7931
8.500 1.1605 0.02072 0.01338 -0.0705 0.0248 0.7983
8.750 1.1835 0.02128 0.01406 -0.0697 0.0239 0.8036
9.000 1.2052 0.02190 0.01476 -0.0688 0.0230 0.8089
9.250 1.2258 0.02265 0.01554 -0.0678 0.0222 0.8147
9.500 1.2444 0.02379 0.01671 -0.0666 0.0216 0.8204
9.750 1.2646 0.02450 0.01758 -0.0654 0.0210 0.8269
10.000 1.2842 0.02530 0.01849 -0.0643 0.0204 0.8345
10.250 1.3028 0.02608 0.01937 -0.0631 0.0198 0.8424
10.500 1.3200 0.02702 0.02035 -0.0617 0.0192 0.8520
10.750 1.3347 0.02838 0.02182 -0.0600 0.0187 0.8645
11.250 1.3570 0.02988 0.02380 -0.0549 0.0178 1.0000
11.500 1.3699 0.03101 0.02503 -0.0531 0.0174 1.0000
11.750 1.3814 0.03217 0.02627 -0.0513 0.0169 1.0000
12.000 1.3920 0.03345 0.02759 -0.0495 0.0166 1.0000
12.250 1.4007 0.03535 0.02951 -0.0476 0.0162 1.0000
12.500 1.4041 0.03710 0.03147 -0.0452 0.0159 1.0000
12.750 1.4067 0.03885 0.03345 -0.0428 0.0156 1.0000
13.000 1.4080 0.04083 0.03562 -0.0407 0.0152 1.0000
13.250 1.4085 0.04296 0.03791 -0.0387 0.0149 1.0000
13.500 1.4084 0.04519 0.04029 -0.0370 0.0146 1.0000
13.750 1.4075 0.04757 0.04279 -0.0356 0.0144 1.0000
14.000 1.4051 0.05017 0.04552 -0.0344 0.0142 1.0000
14.250 1.4012 0.05308 0.04855 -0.0335 0.0140 1.0000
14.500 1.3955 0.05635 0.05193 -0.0330 0.0139 1.0000
14.750 1.3884 0.06000 0.05570 -0.0328 0.0138 1.0000
15.000 1.3769 0.06443 0.06027 -0.0332 0.0137 1.0000
15.250 1.3609 0.06980 0.06580 -0.0343 0.0136 1.0000
15.750 1.3195 0.08357 0.07999 -0.0405 0.0135 1.0000
16.000 1.2979 0.09184 0.08846 -0.0455 0.0135 1.0000
16.250 1.2747 0.10096 0.09778 -0.0513 0.0135 1.0000
16.500 1.2505 0.11112 0.10814 -0.0582 0.0135 1.0000
16.750 1.2115 0.12626 0.12360 -0.0692 0.0137 1.0000
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