NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 500,000 Max Cl/Cd: 57.23 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca000834-il-500000.txt Download as CSV file: xf-naca000834-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6413 0.10628 0.10403 0.0013 1.0000 0.0098
-10.000 -0.6477 0.09988 0.09766 -0.0017 1.0000 0.0099
-9.750 -0.6515 0.09397 0.09177 -0.0051 1.0000 0.0100
-9.500 -0.6547 0.08767 0.08550 -0.0095 1.0000 0.0101
-9.250 -0.6553 0.08009 0.07793 -0.0175 1.0000 0.0100
-9.000 -0.6627 0.07452 0.07229 -0.0219 1.0000 0.0100
-8.750 -0.6739 0.07013 0.06783 -0.0232 1.0000 0.0100
-8.500 -0.6858 0.06562 0.06321 -0.0230 1.0000 0.0100
-8.250 -0.6938 0.06090 0.05835 -0.0226 1.0000 0.0102
-8.000 -0.6977 0.05651 0.05381 -0.0218 1.0000 0.0104
-7.750 -0.6973 0.05265 0.04979 -0.0207 1.0000 0.0106
-7.500 -0.6930 0.04936 0.04634 -0.0194 1.0000 0.0109
-7.250 -0.6870 0.04623 0.04304 -0.0179 1.0000 0.0113
-7.000 -0.6796 0.04322 0.03986 -0.0161 1.0000 0.0117
-6.750 -0.6713 0.04034 0.03679 -0.0139 1.0000 0.0123
-6.500 -0.6617 0.03753 0.03376 -0.0114 1.0000 0.0131
-6.250 -0.6504 0.03485 0.03084 -0.0087 1.0000 0.0144
-6.000 -0.6240 0.03599 0.03174 -0.0065 1.0000 0.0175
-4.250 -0.5181 0.01625 0.01005 0.0105 1.0000 0.0150
-4.000 -0.4954 0.01447 0.00810 0.0119 1.0000 0.0144
-3.750 -0.4737 0.01323 0.00677 0.0134 1.0000 0.0150
-3.500 -0.4521 0.01243 0.00590 0.0146 1.0000 0.0164
-3.250 -0.4218 0.01199 0.00540 0.0139 0.9987 0.0178
-3.000 -0.3906 0.01065 0.00394 0.0130 0.9968 0.0218
-2.750 -0.3554 0.01017 0.00335 0.0112 0.9948 0.0270
-2.500 -0.3254 0.00877 0.00263 0.0101 0.9928 0.2093
-2.250 -0.3015 0.00682 0.00231 0.0096 0.9904 0.6093
-2.000 -0.2718 0.00623 0.00231 0.0091 0.9871 0.7613
-1.750 -0.2413 0.00603 0.00246 0.0091 0.9841 0.8612
-1.500 -0.2066 0.00606 0.00252 0.0079 0.9815 0.8943
-1.250 -0.1770 0.00608 0.00254 0.0078 0.9758 0.9153
-1.000 -0.1411 0.00610 0.00253 0.0061 0.9723 0.9273
-0.750 -0.1025 0.00613 0.00254 0.0039 0.9699 0.9352
-0.500 -0.0695 0.00614 0.00253 0.0028 0.9650 0.9436
-0.250 -0.0348 0.00615 0.00253 0.0014 0.9602 0.9498
0.000 0.0000 0.00614 0.00251 0.0000 0.9560 0.9560
0.250 0.0348 0.00615 0.00253 -0.0014 0.9498 0.9601
0.500 0.0695 0.00614 0.00253 -0.0028 0.9436 0.9650
0.750 0.1025 0.00613 0.00254 -0.0038 0.9352 0.9699
1.000 0.1410 0.00610 0.00253 -0.0061 0.9273 0.9723
1.250 0.1770 0.00608 0.00254 -0.0078 0.9155 0.9758
1.500 0.2065 0.00606 0.00252 -0.0079 0.8941 0.9816
1.750 0.2412 0.00603 0.00246 -0.0090 0.8612 0.9841
2.000 0.2718 0.00623 0.00232 -0.0091 0.7623 0.9871
2.250 0.3014 0.00682 0.00231 -0.0095 0.6087 0.9904
2.500 0.3254 0.00875 0.00263 -0.0101 0.2121 0.9928
2.750 0.3554 0.01017 0.00335 -0.0112 0.0271 0.9949
3.000 0.3907 0.01065 0.00394 -0.0130 0.0218 0.9968
3.250 0.4218 0.01199 0.00541 -0.0139 0.0178 0.9988
3.500 0.4520 0.01243 0.00590 -0.0146 0.0164 1.0000
3.750 0.4736 0.01323 0.00676 -0.0133 0.0150 1.0000
4.000 0.4953 0.01446 0.00810 -0.0119 0.0144 1.0000
4.250 0.5180 0.01625 0.01004 -0.0105 0.0150 1.0000
4.500 0.5380 0.00940 0.00404 -0.0084 0.0276 1.0000
4.750 0.5567 0.01010 0.00497 -0.0064 0.0257 1.0000
5.000 0.5735 0.01107 0.00613 -0.0044 0.0225 1.0000
5.250 0.5883 0.01214 0.00722 -0.0029 0.0199 1.0000
5.500 0.5970 0.01529 0.01058 -0.0004 0.0184 1.0000
6.000 0.6009 0.02331 0.01938 0.0074 0.0175 1.0000
6.250 0.6239 0.02231 0.01861 0.0100 0.0150 1.0000
6.500 0.6320 0.02493 0.02147 0.0131 0.0135 1.0000
6.750 0.6377 0.02796 0.02470 0.0159 0.0127 1.0000
7.000 0.6421 0.03117 0.02810 0.0186 0.0121 1.0000
7.250 0.6452 0.03456 0.03166 0.0209 0.0116 1.0000
7.500 0.6468 0.03820 0.03545 0.0229 0.0113 1.0000
7.750 0.6462 0.04201 0.03939 0.0246 0.0110 1.0000
8.000 0.6429 0.04598 0.04350 0.0262 0.0109 1.0000
8.250 0.6359 0.05010 0.04773 0.0275 0.0107 1.0000
8.500 0.6225 0.05402 0.05175 0.0291 0.0107 1.0000
8.750 0.6024 0.05848 0.05631 0.0292 0.0108 1.0000
9.000 0.5774 0.06555 0.06348 0.0248 0.0111 1.0000
9.250 0.5575 0.07498 0.07291 0.0172 0.0115 1.0000
9.500 0.5475 0.08123 0.07914 0.0142 0.0115 1.0000
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Polar data table (+)
Polar graphs
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