NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-015 (naca16015-il) Reynolds number: 200,000 Max Cl/Cd: 40.35 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16015-il-200000.txt Download as CSV file: xf-naca16015-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-015
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8181 0.06316 0.05905 -0.0468 1.0000 0.0469
-11.250 -0.9164 0.06823 0.06371 -0.0361 1.0000 0.0439
-11.000 -0.9393 0.06563 0.06102 -0.0300 1.0000 0.0432
-10.750 -1.0441 0.05940 0.05395 -0.0091 1.0000 0.0371
-10.500 -1.0593 0.05765 0.05196 -0.0023 1.0000 0.0369
-10.250 -1.0731 0.05489 0.04895 0.0039 1.0000 0.0369
-10.000 -1.0846 0.05152 0.04530 0.0097 1.0000 0.0371
-9.750 -1.0888 0.04837 0.04195 0.0143 1.0000 0.0377
-9.500 -1.0805 0.04693 0.04054 0.0167 1.0000 0.0388
-9.250 -1.0803 0.04464 0.03800 0.0212 1.0000 0.0392
-9.000 -1.0782 0.04210 0.03513 0.0256 1.0000 0.0394
-8.750 -1.0717 0.03994 0.03269 0.0292 1.0000 0.0400
-8.500 -1.0620 0.03802 0.03050 0.0324 1.0000 0.0408
-8.250 -1.0509 0.03655 0.02879 0.0353 1.0000 0.0423
-8.000 -1.0386 0.03520 0.02713 0.0381 1.0000 0.0439
-7.750 -1.0254 0.03410 0.02572 0.0409 1.0000 0.0450
-7.500 -0.9988 0.03144 0.02282 0.0408 1.0000 0.0466
-7.250 -0.9778 0.03024 0.02163 0.0415 1.0000 0.0488
-7.000 -0.9599 0.02947 0.02078 0.0431 1.0000 0.0513
-6.750 -0.9396 0.02861 0.01978 0.0443 1.0000 0.0536
-6.500 -0.9198 0.02791 0.01892 0.0457 1.0000 0.0553
-6.250 -0.8938 0.02644 0.01748 0.0455 1.0000 0.0587
-6.000 -0.8765 0.02581 0.01685 0.0471 1.0000 0.0617
-5.750 -0.8591 0.02520 0.01619 0.0489 1.0000 0.0645
-5.500 -0.8401 0.02481 0.01568 0.0503 0.9996 0.0674
-5.250 -0.8117 0.02387 0.01484 0.0495 0.9969 0.0730
-5.000 -0.7830 0.02355 0.01447 0.0488 0.9945 0.0787
-4.750 -0.7593 0.02288 0.01385 0.0491 0.9906 0.0870
-4.500 -0.7360 0.02235 0.01339 0.0495 0.9872 0.1008
-4.250 -0.7150 0.02157 0.01294 0.0503 0.9845 0.1486
-4.000 -0.7130 0.01992 0.01227 0.0546 0.9804 0.3113
-3.750 -0.7237 0.01793 0.01163 0.0621 0.9758 0.5533
-3.500 -0.6830 0.01832 0.01325 0.0611 0.9749 0.8126
-3.250 -0.6370 0.01961 0.01447 0.0582 0.9732 0.8492
-3.000 -0.6047 0.02068 0.01542 0.0579 0.9709 0.8712
-2.750 -0.5515 0.02237 0.01699 0.0536 0.9690 0.8844
-2.500 -0.4383 0.02568 0.02013 0.0377 0.9726 0.8926
-2.250 -0.3481 0.02823 0.02257 0.0266 0.9743 0.9064
-2.000 -0.2936 0.02925 0.02349 0.0212 0.9734 0.9173
-1.750 -0.2432 0.02960 0.02377 0.0159 0.9722 0.9205
-1.500 -0.2251 0.02969 0.02380 0.0172 0.9677 0.9292
-1.250 -0.1831 0.02975 0.02382 0.0135 0.9650 0.9317
-1.000 -0.1404 0.02984 0.02387 0.0096 0.9626 0.9344
-0.750 -0.1007 0.02994 0.02393 0.0062 0.9603 0.9382
-0.500 -0.0700 0.03010 0.02407 0.0047 0.9581 0.9444
-0.250 -0.0377 0.02998 0.02394 0.0030 0.9531 0.9468
0.000 0.0000 0.02996 0.02392 0.0000 0.9496 0.9496
0.250 0.0376 0.02998 0.02394 -0.0029 0.9468 0.9531
0.500 0.0699 0.03010 0.02406 -0.0047 0.9444 0.9581
0.750 0.1007 0.02993 0.02393 -0.0062 0.9382 0.9603
1.000 0.1403 0.02983 0.02386 -0.0096 0.9344 0.9626
1.250 0.1831 0.02974 0.02381 -0.0135 0.9317 0.9650
1.500 0.2246 0.02968 0.02380 -0.0171 0.9291 0.9678
1.750 0.2431 0.02959 0.02376 -0.0159 0.9205 0.9722
2.000 0.2934 0.02924 0.02348 -0.0212 0.9174 0.9735
2.250 0.3481 0.02822 0.02256 -0.0266 0.9064 0.9743
2.500 0.4383 0.02567 0.02011 -0.0377 0.8926 0.9726
2.750 0.5522 0.02233 0.01696 -0.0537 0.8845 0.9689
3.000 0.6055 0.02064 0.01539 -0.0580 0.8713 0.9708
3.250 0.6370 0.01960 0.01445 -0.0582 0.8491 0.9732
3.750 0.7235 0.01793 0.01162 -0.0620 0.5532 0.9759
4.000 0.7129 0.01991 0.01226 -0.0546 0.3119 0.9805
4.250 0.7149 0.02156 0.01292 -0.0503 0.1489 0.9845
4.500 0.7360 0.02234 0.01338 -0.0495 0.1008 0.9872
4.750 0.7593 0.02287 0.01384 -0.0491 0.0870 0.9906
5.000 0.7829 0.02354 0.01446 -0.0488 0.0787 0.9944
5.250 0.8116 0.02386 0.01483 -0.0495 0.0730 0.9969
5.500 0.8397 0.02480 0.01567 -0.0502 0.0674 0.9996
5.750 0.8590 0.02519 0.01618 -0.0489 0.0645 1.0000
6.000 0.8764 0.02580 0.01685 -0.0471 0.0617 1.0000
6.250 0.8938 0.02643 0.01748 -0.0455 0.0587 1.0000
6.500 0.9198 0.02790 0.01891 -0.0457 0.0553 1.0000
6.750 0.9396 0.02861 0.01978 -0.0443 0.0536 1.0000
7.000 0.9597 0.02945 0.02076 -0.0430 0.0513 1.0000
7.250 0.9777 0.03022 0.02161 -0.0415 0.0488 1.0000
7.500 0.9986 0.03142 0.02281 -0.0408 0.0466 1.0000
7.750 1.0253 0.03409 0.02571 -0.0409 0.0450 1.0000
8.000 1.0384 0.03517 0.02711 -0.0381 0.0439 1.0000
8.250 1.0507 0.03650 0.02873 -0.0353 0.0423 1.0000
8.500 1.0619 0.03799 0.03046 -0.0324 0.0408 1.0000
8.750 1.0715 0.03994 0.03269 -0.0292 0.0400 1.0000
9.000 1.0780 0.04211 0.03515 -0.0256 0.0395 1.0000
9.250 1.0800 0.04469 0.03805 -0.0211 0.0392 1.0000
9.500 1.0789 0.04713 0.04078 -0.0164 0.0389 1.0000
9.750 1.0893 0.04834 0.04190 -0.0144 0.0376 1.0000
10.000 1.0845 0.05153 0.04531 -0.0097 0.0371 1.0000
10.250 1.0731 0.05487 0.04892 -0.0039 0.0369 1.0000
10.500 1.0596 0.05757 0.05188 0.0023 0.0369 1.0000
10.750 1.0442 0.05929 0.05385 0.0091 0.0371 1.0000
11.000 0.8605 0.05595 0.05158 0.0371 0.0430 1.0000
11.250 0.8328 0.05905 0.05481 0.0428 0.0435 1.0000
11.500 0.8048 0.06246 0.05834 0.0478 0.0439 1.0000
11.750 0.7793 0.06629 0.06226 0.0517 0.0444 1.0000
12.000 0.6776 0.09731 0.09379 0.0508 0.0724 1.0000
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Polar data table (+)
Polar graphs
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