NACA 16-006 (naca16006-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-006 (naca16006-il) Reynolds number: 200,000 Max Cl/Cd: 25.6 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16006-il-200000.txt Download as CSV file: xf-naca16006-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5311 0.08755 0.08415 -0.0110 1.0000 0.0287
-8.750 -0.5355 0.08301 0.07963 -0.0127 1.0000 0.0292
-8.500 -0.5416 0.07830 0.07495 -0.0146 1.0000 0.0296
-8.250 -0.5503 0.07339 0.07007 -0.0173 1.0000 0.0297
-8.000 -0.5628 0.06853 0.06522 -0.0203 1.0000 0.0294
-7.750 -0.5754 0.06433 0.06100 -0.0208 1.0000 0.0294
-7.500 -0.5828 0.05985 0.05647 -0.0212 1.0000 0.0298
-7.250 -0.5876 0.05537 0.05191 -0.0210 1.0000 0.0304
-7.000 -0.5900 0.05100 0.04744 -0.0203 1.0000 0.0313
-6.500 -0.6296 0.05478 0.05060 -0.0155 1.0000 0.0320
-6.250 -0.6139 0.05319 0.04852 -0.0132 1.0000 0.0354
-6.000 -0.6037 0.05122 0.04617 -0.0105 1.0000 0.0358
-4.500 -0.5243 0.01759 0.01199 0.0007 1.0000 0.0675
-4.250 -0.5103 0.01553 0.00966 0.0028 1.0000 0.0789
-3.750 -0.4669 0.02144 0.01384 0.0087 1.0000 0.0328
-3.500 -0.4419 0.01900 0.01105 0.0102 1.0000 0.0307
-3.250 -0.4164 0.01723 0.00896 0.0114 1.0000 0.0316
-3.000 -0.3923 0.01622 0.00776 0.0125 1.0000 0.0370
-2.750 -0.3687 0.01458 0.00612 0.0136 1.0000 0.0392
-2.500 -0.3463 0.01356 0.00509 0.0148 1.0000 0.0446
-2.250 -0.3240 0.01267 0.00418 0.0159 1.0000 0.0575
-2.000 -0.3011 0.01177 0.00340 0.0169 1.0000 0.0957
-1.750 -0.1011 0.00971 0.00408 -0.0164 1.0000 1.0000
-1.500 -0.0845 0.00958 0.00388 -0.0145 1.0000 1.0000
-1.250 -0.0689 0.00947 0.00373 -0.0125 1.0000 1.0000
-1.000 -0.0539 0.00939 0.00360 -0.0103 1.0000 1.0000
-0.750 -0.0396 0.00933 0.00349 -0.0079 1.0000 1.0000
-0.500 -0.0260 0.00928 0.00342 -0.0053 1.0000 1.0000
-0.250 -0.0129 0.00925 0.00338 -0.0027 1.0000 1.0000
0.000 0.0000 0.00925 0.00337 0.0000 1.0000 1.0000
0.250 0.0129 0.00925 0.00338 0.0027 1.0000 1.0000
0.500 0.0260 0.00928 0.00342 0.0053 1.0000 1.0000
0.750 0.0396 0.00932 0.00349 0.0079 1.0000 1.0000
1.000 0.0539 0.00939 0.00360 0.0103 1.0000 1.0000
1.250 0.0689 0.00947 0.00372 0.0125 1.0000 1.0000
1.500 0.0846 0.00957 0.00388 0.0145 1.0000 1.0000
1.750 0.1012 0.00970 0.00408 0.0163 1.0000 1.0000
2.000 0.3008 0.01175 0.00339 -0.0168 0.0967 1.0000
2.250 0.3237 0.01266 0.00418 -0.0159 0.0576 1.0000
2.500 0.3459 0.01356 0.00508 -0.0147 0.0445 1.0000
2.750 0.3683 0.01458 0.00611 -0.0135 0.0392 1.0000
3.000 0.3920 0.01621 0.00775 -0.0124 0.0370 1.0000
3.250 0.4161 0.01722 0.00895 -0.0113 0.0316 1.0000
3.500 0.4415 0.01898 0.01103 -0.0101 0.0308 1.0000
3.750 0.4665 0.02143 0.01382 -0.0086 0.0328 1.0000
4.000 0.5046 0.02671 0.02021 -0.0045 0.0933 1.0000
4.250 0.5220 0.02863 0.02231 -0.0029 0.0794 1.0000
4.500 0.5382 0.03073 0.02467 -0.0010 0.0678 1.0000
4.750 0.5545 0.03355 0.02745 0.0003 0.0633 1.0000
5.000 0.5687 0.03548 0.02993 0.0032 0.0540 1.0000
5.250 0.5817 0.03897 0.03326 0.0042 0.0498 1.0000
5.500 0.5936 0.04076 0.03570 0.0076 0.0407 1.0000
5.750 0.6041 0.04364 0.03854 0.0090 0.0375 1.0000
6.000 0.6035 0.05121 0.04616 0.0105 0.0358 1.0000
6.250 0.6138 0.05318 0.04851 0.0132 0.0354 1.0000
6.500 0.6296 0.05478 0.05060 0.0155 0.0320 1.0000
6.750 0.6370 0.05851 0.05452 0.0167 0.0303 1.0000
7.000 0.6427 0.06236 0.05851 0.0173 0.0290 1.0000
7.250 0.6471 0.06629 0.06256 0.0176 0.0280 1.0000
7.500 0.6501 0.07029 0.06665 0.0173 0.0272 1.0000
7.750 0.6518 0.07433 0.07076 0.0167 0.0266 1.0000
8.000 0.6522 0.07845 0.07499 0.0156 0.0260 1.0000
8.250 0.6512 0.08255 0.07911 0.0143 0.0256 1.0000
8.500 0.6475 0.08657 0.08315 0.0129 0.0252 1.0000
8.750 0.6445 0.09107 0.08763 0.0099 0.0250 1.0000
9.000 0.6439 0.09533 0.09187 0.0083 0.0245 1.0000
9.250 0.6427 0.09993 0.09646 0.0084 0.0239 1.0000
9.500 0.5250 0.09620 0.09275 0.0084 0.0277 1.0000
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Polar data table (+)
Polar graphs
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