NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 200,000 Max Cl/Cd: 36.02 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca000834-il-200000-n5.txt Download as CSV file: xf-naca000834-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008-34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5198 0.08601 0.08275 -0.0176 1.0000 0.0167
-9.250 -0.5259 0.08030 0.07705 -0.0205 1.0000 0.0167
-9.000 -0.5353 0.07392 0.07067 -0.0248 1.0000 0.0167
-8.750 -0.5485 0.06857 0.06527 -0.0280 1.0000 0.0167
-8.500 -0.5642 0.06404 0.06067 -0.0296 1.0000 0.0167
-8.250 -0.5794 0.06021 0.05677 -0.0293 1.0000 0.0167
-8.000 -0.5924 0.05652 0.05299 -0.0278 1.0000 0.0167
-7.750 -0.6000 0.05249 0.04882 -0.0265 1.0000 0.0167
-7.250 -0.6587 0.05385 0.04966 -0.0196 1.0000 0.0091
-7.000 -0.6566 0.04988 0.04551 -0.0182 1.0000 0.0086
-6.750 -0.6511 0.04611 0.04149 -0.0164 1.0000 0.0082
-6.500 -0.6433 0.04245 0.03756 -0.0142 1.0000 0.0078
-6.250 -0.6337 0.03891 0.03370 -0.0117 1.0000 0.0073
-6.000 -0.6224 0.03544 0.02988 -0.0090 1.0000 0.0069
-5.750 -0.6091 0.03200 0.02604 -0.0062 1.0000 0.0065
-5.500 -0.5934 0.02845 0.02200 -0.0032 1.0000 0.0060
-5.250 -0.5750 0.02564 0.01876 -0.0007 1.0000 0.0057
-5.000 -0.5552 0.02346 0.01620 0.0014 1.0000 0.0055
-4.750 -0.5346 0.02149 0.01391 0.0031 1.0000 0.0054
-4.500 -0.5135 0.01952 0.01155 0.0048 1.0000 0.0055
-4.250 -0.4928 0.01783 0.00968 0.0064 1.0000 0.0056
-4.000 -0.4731 0.01647 0.00821 0.0080 1.0000 0.0059
-3.750 -0.4534 0.01542 0.00707 0.0096 1.0000 0.0064
-3.500 -0.4335 0.01452 0.00606 0.0111 1.0000 0.0074
-3.250 -0.4126 0.01371 0.00507 0.0125 1.0000 0.0102
-3.000 -0.3913 0.01319 0.00458 0.0134 1.0000 0.0267
-2.750 -0.3690 0.01266 0.00400 0.0143 1.0000 0.0403
-2.500 -0.3438 0.01096 0.00337 0.0136 0.9978 0.2872
-2.250 -0.3247 0.00902 0.00325 0.0148 0.9953 0.6860
-2.000 -0.2982 0.00877 0.00342 0.0159 0.9920 0.8150
-1.750 -0.2662 0.00883 0.00336 0.0155 0.9885 0.8638
-1.500 -0.2318 0.00902 0.00354 0.0148 0.9863 0.9068
-1.250 -0.1964 0.00909 0.00352 0.0132 0.9821 0.9217
-1.000 -0.1580 0.00915 0.00350 0.0108 0.9785 0.9317
-0.750 -0.1195 0.00919 0.00349 0.0083 0.9749 0.9408
-0.500 -0.0806 0.00923 0.00347 0.0057 0.9702 0.9482
-0.250 -0.0396 0.00925 0.00345 0.0027 0.9664 0.9547
0.000 0.0000 0.00926 0.00346 0.0000 0.9607 0.9607
0.250 0.0396 0.00925 0.00346 -0.0027 0.9547 0.9664
0.500 0.0806 0.00923 0.00347 -0.0057 0.9482 0.9702
0.750 0.1195 0.00919 0.00349 -0.0083 0.9408 0.9749
1.000 0.1581 0.00915 0.00350 -0.0108 0.9317 0.9786
1.250 0.1964 0.00909 0.00352 -0.0132 0.9217 0.9821
1.500 0.2318 0.00902 0.00355 -0.0148 0.9075 0.9863
1.750 0.2663 0.00883 0.00336 -0.0155 0.8635 0.9885
2.000 0.2983 0.00877 0.00342 -0.0160 0.8145 0.9920
2.250 0.3249 0.00902 0.00325 -0.0149 0.6861 0.9953
2.500 0.3440 0.01094 0.00337 -0.0137 0.2913 0.9978
2.750 0.3691 0.01266 0.00400 -0.0144 0.0403 1.0000
3.000 0.3914 0.01319 0.00458 -0.0134 0.0268 1.0000
3.250 0.4127 0.01373 0.00508 -0.0125 0.0101 1.0000
3.500 0.4336 0.01453 0.00606 -0.0111 0.0074 1.0000
3.750 0.4535 0.01543 0.00707 -0.0096 0.0063 1.0000
4.000 0.4731 0.01648 0.00821 -0.0080 0.0058 1.0000
4.250 0.4929 0.01784 0.00969 -0.0064 0.0056 1.0000
4.500 0.5136 0.01952 0.01155 -0.0048 0.0055 1.0000
4.750 0.5347 0.02149 0.01391 -0.0031 0.0054 1.0000
5.000 0.5553 0.02346 0.01620 -0.0014 0.0055 1.0000
5.250 0.5751 0.02565 0.01876 0.0006 0.0057 1.0000
5.500 0.5934 0.02846 0.02202 0.0031 0.0060 1.0000
5.750 0.6092 0.03199 0.02603 0.0061 0.0065 1.0000
6.000 0.6225 0.03544 0.02988 0.0090 0.0069 1.0000
6.250 0.6337 0.03891 0.03371 0.0117 0.0073 1.0000
6.500 0.6433 0.04246 0.03756 0.0142 0.0078 1.0000
6.750 0.6511 0.04611 0.04150 0.0164 0.0082 1.0000
7.000 0.6566 0.04988 0.04550 0.0182 0.0086 1.0000
7.250 0.6587 0.05385 0.04966 0.0196 0.0091 1.0000
7.500 0.6673 0.05933 0.05550 0.0213 0.0128 1.0000
7.750 0.6673 0.06380 0.06013 0.0217 0.0134 1.0000
8.000 0.6649 0.06827 0.06473 0.0215 0.0138 1.0000
8.250 0.6597 0.07283 0.06939 0.0206 0.0141 1.0000
8.500 0.6501 0.07736 0.07398 0.0191 0.0143 1.0000
8.750 0.6417 0.08304 0.07969 0.0144 0.0146 1.0000
9.000 0.6371 0.08904 0.08565 0.0090 0.0150 1.0000
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Polar data table (+)
Polar graphs
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