NACA 16-006 (naca16006-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NACA 16-006 (naca16006-il) Reynolds number: 100,000 Max Cl/Cd: 20.56 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16006-il-100000.txt Download as CSV file: xf-naca16006-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-006
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6566 0.08898 0.08412 -0.0122 1.0000 0.0728
-8.000 -0.6640 0.08515 0.08020 -0.0161 1.0000 0.0738
-7.750 -0.6716 0.08232 0.07723 -0.0183 1.0000 0.0745
-7.500 -0.6571 0.07642 0.07152 -0.0147 1.0000 0.0820
-7.250 -0.6607 0.07329 0.06813 -0.0171 1.0000 0.0870
-7.000 -0.6571 0.06821 0.06305 -0.0165 1.0000 0.0903
-6.750 -0.6490 0.06477 0.05958 -0.0154 1.0000 0.0973
-6.500 -0.6458 0.06083 0.05548 -0.0149 1.0000 0.1042
-6.250 -0.6418 0.05812 0.05244 -0.0139 1.0000 0.1156
-5.500 -0.6138 0.04802 0.04221 -0.0088 1.0000 0.1580
-5.250 -0.5745 0.03113 0.02585 -0.0074 1.0000 0.1853
-4.500 -0.5754 0.03829 0.03227 0.0012 1.0000 0.2878
-4.250 -0.5610 0.03489 0.02885 0.0036 1.0000 0.3130
-4.000 -0.4834 0.02690 0.01777 0.0036 1.0000 0.0587
-3.750 -0.4603 0.02533 0.01565 0.0056 1.0000 0.0621
-3.500 -0.4343 0.02301 0.01294 0.0069 1.0000 0.0612
-3.250 -0.4076 0.02097 0.01067 0.0080 1.0000 0.0614
-3.000 -0.3818 0.01871 0.00846 0.0088 1.0000 0.0647
-2.750 -0.3588 0.01745 0.00720 0.0101 1.0000 0.0760
-2.500 -0.1657 0.01301 0.00550 -0.0189 1.0000 1.0000
-2.250 -0.1472 0.01281 0.00511 -0.0175 1.0000 1.0000
-2.000 -0.1293 0.01265 0.00478 -0.0159 1.0000 1.0000
-1.750 -0.1119 0.01250 0.00451 -0.0143 1.0000 1.0000
-1.500 -0.0950 0.01238 0.00429 -0.0125 1.0000 1.0000
-1.250 -0.0786 0.01228 0.00411 -0.0105 1.0000 1.0000
-1.000 -0.0625 0.01220 0.00397 -0.0085 1.0000 1.0000
-0.750 -0.0466 0.01214 0.00383 -0.0065 1.0000 1.0000
-0.500 -0.0309 0.01210 0.00375 -0.0044 1.0000 1.0000
-0.250 -0.0154 0.01208 0.00370 -0.0022 1.0000 1.0000
0.000 0.0000 0.01207 0.00369 0.0000 1.0000 1.0000
0.250 0.0154 0.01207 0.00370 0.0022 1.0000 1.0000
0.500 0.0309 0.01210 0.00375 0.0044 1.0000 1.0000
0.750 0.0466 0.01214 0.00383 0.0065 1.0000 1.0000
1.000 0.0625 0.01220 0.00396 0.0085 1.0000 1.0000
1.250 0.0787 0.01228 0.00411 0.0105 1.0000 1.0000
1.500 0.0951 0.01238 0.00429 0.0125 1.0000 1.0000
1.750 0.1120 0.01250 0.00451 0.0143 1.0000 1.0000
2.000 0.1294 0.01264 0.00478 0.0159 1.0000 1.0000
2.250 0.1474 0.01281 0.00511 0.0175 1.0000 1.0000
2.500 0.1658 0.01300 0.00550 0.0188 1.0000 1.0000
2.750 0.3585 0.01744 0.00719 -0.0100 0.0760 1.0000
3.000 0.3815 0.01870 0.00845 -0.0087 0.0647 1.0000
3.250 0.4073 0.02096 0.01066 -0.0079 0.0614 1.0000
3.500 0.4340 0.02299 0.01292 -0.0068 0.0612 1.0000
3.750 0.4599 0.02532 0.01564 -0.0055 0.0621 1.0000
4.000 0.4831 0.02690 0.01776 -0.0036 0.0588 1.0000
5.250 0.6049 0.04535 0.03944 0.0068 0.1837 1.0000
5.500 0.5819 0.03487 0.02950 0.0095 0.1667 1.0000
5.750 0.5870 0.03750 0.03236 0.0117 0.1452 1.0000
6.250 0.5942 0.04494 0.04003 0.0151 0.1206 1.0000
6.500 0.6459 0.06084 0.05548 0.0149 0.1042 1.0000
6.750 0.6491 0.06478 0.05959 0.0154 0.0973 1.0000
7.000 0.6020 0.05803 0.05323 0.0192 0.1001 1.0000
7.250 0.6608 0.07329 0.06813 0.0171 0.0870 1.0000
7.500 0.6574 0.07645 0.07155 0.0146 0.0819 1.0000
7.750 0.6719 0.08234 0.07726 0.0182 0.0745 1.0000
8.000 0.6642 0.08517 0.08023 0.0159 0.0738 1.0000
8.250 0.6569 0.08903 0.08417 0.0120 0.0727 1.0000
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Polar data table (+)
Polar graphs
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