NACA 16009 (naca16009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16009 (naca16009-il) Reynolds number: 1,000,000 Max Cl/Cd: 47.07 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16009-il-1000000-n5.txt Download as CSV file: xf-naca16009-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6648 0.07769 0.07613 -0.0369 1.0000 0.0020
-10.000 -0.6854 0.07178 0.07017 -0.0399 1.0000 0.0020
-9.750 -0.7091 0.06780 0.06615 -0.0383 1.0000 0.0019
-8.750 -0.8460 0.02448 0.02069 -0.0170 0.9882 0.0020
-8.500 -0.8290 0.02170 0.01751 -0.0157 0.9866 0.0021
-8.250 -0.8058 0.02025 0.01583 -0.0155 0.9854 0.0023
-8.000 -0.7804 0.01914 0.01454 -0.0156 0.9845 0.0023
-7.750 -0.7588 0.01675 0.01179 -0.0150 0.9836 0.0026
-7.500 -0.7315 0.01595 0.01088 -0.0155 0.9829 0.0029
-7.250 -0.7032 0.01541 0.01026 -0.0162 0.9823 0.0030
-7.000 -0.6762 0.01477 0.00954 -0.0165 0.9814 0.0032
-6.750 -0.6547 0.01417 0.00886 -0.0154 0.9786 0.0035
-6.500 -0.6304 0.01349 0.00805 -0.0150 0.9766 0.0037
-6.250 -0.6048 0.01288 0.00735 -0.0149 0.9748 0.0041
-6.000 -0.5779 0.01240 0.00681 -0.0150 0.9733 0.0046
-5.750 -0.5505 0.01199 0.00635 -0.0153 0.9719 0.0050
-5.500 -0.5232 0.01156 0.00586 -0.0155 0.9706 0.0052
-5.250 -0.4983 0.01076 0.00494 -0.0151 0.9691 0.0059
-5.000 -0.4755 0.01025 0.00435 -0.0142 0.9665 0.0066
-4.750 -0.4517 0.00991 0.00394 -0.0135 0.9635 0.0072
-4.500 -0.4261 0.00961 0.00359 -0.0132 0.9612 0.0077
-4.250 -0.3996 0.00934 0.00329 -0.0132 0.9591 0.0084
-4.000 -0.3728 0.00908 0.00299 -0.0131 0.9573 0.0089
-3.750 -0.3452 0.00885 0.00271 -0.0133 0.9557 0.0095
-3.500 -0.3204 0.00866 0.00251 -0.0127 0.9527 0.0123
-3.250 -0.2959 0.00841 0.00230 -0.0122 0.9495 0.0257
-3.000 -0.2704 0.00817 0.00213 -0.0119 0.9468 0.0454
-2.750 -0.2441 0.00795 0.00198 -0.0118 0.9444 0.0663
-2.500 -0.2175 0.00769 0.00183 -0.0118 0.9424 0.0973
-2.250 -0.1953 0.00731 0.00169 -0.0109 0.9386 0.1666
-2.000 -0.1787 0.00646 0.00149 -0.0090 0.9341 0.3474
-1.750 -0.1654 0.00541 0.00122 -0.0064 0.9301 0.5672
-1.500 -0.1482 0.00489 0.00110 -0.0042 0.9258 0.6777
-1.250 -0.1268 0.00463 0.00104 -0.0029 0.9216 0.7366
-1.000 -0.1046 0.00439 0.00102 -0.0016 0.9181 0.7999
-0.750 -0.0800 0.00425 0.00106 -0.0008 0.9152 0.8531
-0.500 -0.0548 0.00424 0.00113 -0.0002 0.9109 0.8810
-0.250 -0.0276 0.00424 0.00117 0.0000 0.9067 0.8942
0.000 0.0000 0.00424 0.00114 0.0000 0.9023 0.9024
0.250 0.0276 0.00424 0.00117 0.0000 0.8942 0.9067
0.500 0.0548 0.00424 0.00113 0.0002 0.8810 0.9109
0.750 0.0800 0.00425 0.00106 0.0008 0.8535 0.9152
1.000 0.1045 0.00438 0.00102 0.0016 0.7998 0.9181
1.250 0.1267 0.00463 0.00104 0.0029 0.7361 0.9216
1.500 0.1482 0.00489 0.00110 0.0042 0.6782 0.9257
1.750 0.1658 0.00539 0.00121 0.0063 0.5719 0.9300
2.000 0.1791 0.00643 0.00148 0.0089 0.3539 0.9340
2.250 0.1953 0.00731 0.00169 0.0109 0.1666 0.9386
2.500 0.2175 0.00770 0.00183 0.0118 0.0966 0.9424
2.750 0.2441 0.00795 0.00198 0.0118 0.0662 0.9444
3.000 0.2705 0.00817 0.00213 0.0119 0.0457 0.9467
3.250 0.2959 0.00841 0.00230 0.0122 0.0256 0.9495
3.500 0.3204 0.00867 0.00251 0.0127 0.0122 0.9527
3.750 0.3452 0.00885 0.00271 0.0133 0.0095 0.9557
4.000 0.3728 0.00908 0.00298 0.0131 0.0089 0.9572
4.250 0.3996 0.00934 0.00329 0.0132 0.0084 0.9591
4.500 0.4261 0.00961 0.00359 0.0132 0.0077 0.9611
4.750 0.4516 0.00992 0.00394 0.0135 0.0072 0.9636
5.000 0.4753 0.01025 0.00435 0.0142 0.0067 0.9666
5.250 0.4983 0.01077 0.00495 0.0151 0.0059 0.9692
5.500 0.5232 0.01155 0.00585 0.0155 0.0052 0.9706
5.750 0.5505 0.01199 0.00635 0.0153 0.0050 0.9719
6.000 0.5778 0.01242 0.00683 0.0150 0.0046 0.9733
6.250 0.6048 0.01285 0.00732 0.0149 0.0041 0.9748
6.500 0.6303 0.01349 0.00805 0.0150 0.0037 0.9766
6.750 0.6547 0.01415 0.00884 0.0154 0.0035 0.9787
7.000 0.6759 0.01479 0.00956 0.0166 0.0033 0.9815
7.250 0.7034 0.01544 0.01030 0.0162 0.0031 0.9823
7.500 0.7317 0.01596 0.01089 0.0155 0.0029 0.9830
7.750 0.7588 0.01677 0.01181 0.0150 0.0026 0.9836
8.000 0.7800 0.01920 0.01461 0.0157 0.0023 0.9845
8.250 0.8060 0.02014 0.01571 0.0155 0.0023 0.9854
8.500 0.8289 0.02172 0.01753 0.0158 0.0021 0.9866
8.750 0.8460 0.02449 0.02070 0.0170 0.0020 0.9882
9.250 0.7535 0.06020 0.05839 0.0308 0.0019 0.9984
9.500 0.7358 0.06540 0.06370 0.0330 0.0019 1.0000
9.750 0.7092 0.06781 0.06616 0.0383 0.0019 1.0000
10.000 0.6854 0.07184 0.07023 0.0398 0.0020 1.0000
10.250 0.6656 0.07765 0.07609 0.0368 0.0020 1.0000
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Polar data table (+)
Polar graphs
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