NACA 16009 (naca16009-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16009 (naca16009-il) Reynolds number: 500,000 Max Cl/Cd: 38.01 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16009-il-500000-n5.txt Download as CSV file: xf-naca16009-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16009
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6315 0.08401 0.08178 -0.0317 1.0000 0.0037
-9.750 -0.6473 0.07710 0.07487 -0.0375 1.0000 0.0036
-9.500 -0.6673 0.07229 0.07002 -0.0383 1.0000 0.0036
-9.250 -0.6902 0.06890 0.06659 -0.0355 1.0000 0.0035
-9.000 -0.7145 0.06639 0.06405 -0.0302 1.0000 0.0035
-8.750 -0.7333 0.06303 0.06060 -0.0258 1.0000 0.0035
-8.500 -0.7501 0.05952 0.05699 -0.0211 1.0000 0.0034
-8.250 -0.7542 0.05376 0.05100 -0.0195 0.9981 0.0034
-8.000 -0.7521 0.04698 0.04390 -0.0183 0.9953 0.0034
-7.750 -0.7490 0.04003 0.03653 -0.0159 0.9928 0.0034
-7.500 -0.7457 0.03307 0.02903 -0.0122 0.9892 0.0036
-7.250 -0.7351 0.02743 0.02279 -0.0093 0.9865 0.0040
-7.000 -0.7163 0.02400 0.01887 -0.0078 0.9848 0.0044
-6.750 -0.6926 0.02177 0.01626 -0.0073 0.9836 0.0047
-6.500 -0.6657 0.02045 0.01465 -0.0074 0.9827 0.0051
-6.250 -0.6395 0.01862 0.01252 -0.0075 0.9819 0.0058
-6.000 -0.6181 0.01715 0.01086 -0.0064 0.9797 0.0063
-5.750 -0.5950 0.01601 0.00956 -0.0056 0.9774 0.0066
-5.500 -0.5699 0.01508 0.00852 -0.0053 0.9754 0.0071
-5.250 -0.5435 0.01430 0.00764 -0.0052 0.9738 0.0078
-5.000 -0.5163 0.01362 0.00687 -0.0054 0.9723 0.0086
-4.750 -0.4882 0.01302 0.00618 -0.0057 0.9711 0.0093
-4.500 -0.4585 0.01265 0.00571 -0.0065 0.9701 0.0102
-4.250 -0.4297 0.01205 0.00502 -0.0070 0.9692 0.0110
-4.000 -0.4044 0.01157 0.00443 -0.0066 0.9670 0.0121
-3.750 -0.3818 0.01124 0.00406 -0.0056 0.9634 0.0150
-3.500 -0.3544 0.01091 0.00375 -0.0057 0.9614 0.0257
-3.250 -0.3261 0.01057 0.00349 -0.0062 0.9597 0.0484
-3.000 -0.2977 0.01021 0.00324 -0.0067 0.9582 0.0833
-2.750 -0.2705 0.00969 0.00300 -0.0070 0.9568 0.1578
-2.500 -0.2536 0.00854 0.00271 -0.0055 0.9539 0.3730
-2.250 -0.2448 0.00751 0.00245 -0.0018 0.9483 0.5719
-2.000 -0.2306 0.00666 0.00233 0.0011 0.9451 0.7492
-1.750 -0.2030 0.00647 0.00234 0.0013 0.9436 0.8106
-1.500 -0.1722 0.00642 0.00234 0.0007 0.9425 0.8421
-1.250 -0.1462 0.00653 0.00255 0.0014 0.9394 0.8833
-1.000 -0.1185 0.00671 0.00277 0.0018 0.9366 0.9068
-0.750 -0.0913 0.00676 0.00281 0.0020 0.9339 0.9165
-0.500 -0.0585 0.00681 0.00283 0.0008 0.9322 0.9198
-0.250 -0.0268 0.00681 0.00282 -0.0001 0.9304 0.9230
0.000 0.0000 0.00679 0.00279 0.0000 0.9274 0.9274
0.250 0.0268 0.00681 0.00282 0.0001 0.9230 0.9304
0.500 0.0585 0.00681 0.00283 -0.0008 0.9198 0.9321
0.750 0.0913 0.00676 0.00281 -0.0020 0.9165 0.9338
1.000 0.1185 0.00671 0.00277 -0.0018 0.9068 0.9366
1.250 0.1462 0.00653 0.00255 -0.0014 0.8834 0.9394
1.500 0.1722 0.00642 0.00234 -0.0007 0.8424 0.9425
1.750 0.2030 0.00647 0.00234 -0.0013 0.8106 0.9436
2.000 0.2306 0.00665 0.00234 -0.0011 0.7504 0.9451
2.250 0.2449 0.00751 0.00245 0.0018 0.5724 0.9483
2.500 0.2535 0.00855 0.00271 0.0055 0.3716 0.9539
2.750 0.2704 0.00970 0.00301 0.0070 0.1552 0.9568
3.000 0.2977 0.01021 0.00324 0.0067 0.0835 0.9582
3.250 0.3260 0.01057 0.00349 0.0062 0.0480 0.9597
3.500 0.3543 0.01091 0.00375 0.0057 0.0255 0.9614
3.750 0.3817 0.01124 0.00406 0.0056 0.0150 0.9635
4.000 0.4041 0.01157 0.00443 0.0066 0.0121 0.9670
4.250 0.4295 0.01205 0.00501 0.0070 0.0110 0.9692
4.500 0.4585 0.01264 0.00570 0.0065 0.0102 0.9701
4.750 0.4883 0.01303 0.00618 0.0057 0.0093 0.9712
5.000 0.5164 0.01362 0.00687 0.0053 0.0086 0.9724
5.250 0.5436 0.01430 0.00764 0.0052 0.0078 0.9738
5.500 0.5697 0.01507 0.00851 0.0053 0.0071 0.9754
5.750 0.5949 0.01600 0.00955 0.0056 0.0066 0.9774
6.000 0.6180 0.01715 0.01085 0.0064 0.0063 0.9797
6.250 0.6394 0.01863 0.01253 0.0075 0.0057 0.9819
6.500 0.6656 0.02046 0.01467 0.0075 0.0051 0.9827
6.750 0.6926 0.02175 0.01624 0.0073 0.0047 0.9837
7.000 0.7163 0.02402 0.01889 0.0078 0.0044 0.9849
7.250 0.7352 0.02744 0.02280 0.0093 0.0040 0.9866
7.500 0.7458 0.03311 0.02907 0.0122 0.0036 0.9893
7.750 0.7491 0.04006 0.03656 0.0158 0.0034 0.9928
8.000 0.7522 0.04700 0.04391 0.0183 0.0034 0.9954
8.250 0.7543 0.05377 0.05102 0.0195 0.0034 0.9981
8.500 0.7501 0.05951 0.05698 0.0212 0.0034 1.0000
8.750 0.7333 0.06302 0.06060 0.0258 0.0035 1.0000
9.000 0.7145 0.06638 0.06404 0.0302 0.0035 1.0000
9.250 0.6902 0.06891 0.06661 0.0355 0.0035 1.0000
9.500 0.6675 0.07231 0.07005 0.0382 0.0036 1.0000
9.750 0.6477 0.07713 0.07491 0.0374 0.0036 1.0000
10.000 0.6320 0.08409 0.08186 0.0316 0.0037 1.0000
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Polar data table (+)
Polar graphs
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