NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 100,000 Max Cl/Cd: 24.74 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca000834-il-100000.txt Download as CSV file: xf-naca000834-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5375 0.09124 0.08671 -0.0117 1.0000 0.1113
-9.000 -0.5454 0.08679 0.08230 -0.0136 1.0000 0.1163
-8.750 -0.6586 0.09006 0.08540 -0.0101 1.0000 0.1007
-8.500 -0.6725 0.08493 0.08029 -0.0149 1.0000 0.1030
-8.250 -0.6943 0.08062 0.07587 -0.0188 1.0000 0.1052
-8.000 -0.7212 0.07854 0.07334 -0.0204 1.0000 0.1064
-7.750 -0.6928 0.07231 0.06750 -0.0186 1.0000 0.1174
-7.500 -0.6906 0.06806 0.06323 -0.0180 1.0000 0.1244
-5.250 -0.5869 0.03223 0.02382 -0.0046 1.0000 0.0635
-5.000 -0.5636 0.02986 0.02067 -0.0017 1.0000 0.0548
-4.750 -0.5424 0.02682 0.01742 -0.0006 1.0000 0.0574
-4.500 -0.5179 0.02469 0.01495 0.0009 1.0000 0.0570
-4.250 -0.4915 0.02277 0.01278 0.0022 1.0000 0.0558
-4.000 -0.4664 0.02085 0.01082 0.0034 1.0000 0.0568
-3.750 -0.4441 0.01930 0.00931 0.0048 1.0000 0.0598
-3.500 -0.4238 0.01816 0.00813 0.0065 1.0000 0.0680
-3.250 -0.4050 0.01701 0.00697 0.0084 1.0000 0.0796
-3.000 -0.3862 0.01561 0.00571 0.0103 1.0000 0.1097
-2.750 -0.2112 0.01527 0.00805 -0.0079 1.0000 0.9778
-2.500 -0.1508 0.01482 0.00728 -0.0154 1.0000 0.9929
-2.250 -0.1093 0.01433 0.00654 -0.0193 1.0000 1.0000
-2.000 -0.0925 0.01397 0.00609 -0.0184 1.0000 1.0000
-1.750 -0.0763 0.01366 0.00572 -0.0173 1.0000 1.0000
-1.500 -0.0610 0.01341 0.00541 -0.0158 1.0000 1.0000
-1.250 -0.0471 0.01319 0.00516 -0.0140 1.0000 1.0000
-1.000 -0.0350 0.01303 0.00496 -0.0118 1.0000 1.0000
-0.750 -0.0246 0.01290 0.00480 -0.0092 1.0000 1.0000
-0.500 -0.0153 0.01281 0.00470 -0.0064 1.0000 1.0000
-0.250 -0.0073 0.01275 0.00465 -0.0033 1.0000 1.0000
0.000 0.0000 0.01273 0.00463 0.0000 1.0000 1.0000
0.250 0.0073 0.01275 0.00465 0.0033 1.0000 1.0000
0.500 0.0153 0.01281 0.00470 0.0064 1.0000 1.0000
0.750 0.0246 0.01290 0.00480 0.0092 1.0000 1.0000
1.000 0.0350 0.01302 0.00496 0.0118 1.0000 1.0000
1.250 0.0471 0.01319 0.00515 0.0140 1.0000 1.0000
1.500 0.0610 0.01340 0.00540 0.0158 1.0000 1.0000
1.750 0.0763 0.01366 0.00571 0.0172 1.0000 1.0000
2.000 0.0925 0.01397 0.00609 0.0184 1.0000 1.0000
2.250 0.1094 0.01433 0.00654 0.0193 1.0000 1.0000
2.500 0.1508 0.01481 0.00727 0.0154 0.9929 1.0000
2.750 0.2111 0.01527 0.00804 0.0079 0.9779 1.0000
3.000 0.3862 0.01561 0.00571 -0.0103 0.1098 1.0000
3.250 0.4050 0.01701 0.00697 -0.0084 0.0796 1.0000
3.500 0.4238 0.01815 0.00812 -0.0065 0.0680 1.0000
3.750 0.4440 0.01930 0.00930 -0.0048 0.0598 1.0000
4.000 0.4664 0.02085 0.01081 -0.0033 0.0568 1.0000
4.250 0.4915 0.02277 0.01277 -0.0022 0.0558 1.0000
4.500 0.5179 0.02469 0.01495 -0.0009 0.0570 1.0000
4.750 0.5423 0.02683 0.01741 0.0006 0.0572 1.0000
5.000 0.5636 0.02983 0.02064 0.0018 0.0548 1.0000
5.250 0.5869 0.03222 0.02381 0.0046 0.0635 1.0000
5.500 0.6165 0.03799 0.03032 0.0074 0.1057 1.0000
7.750 0.6267 0.06242 0.05795 0.0224 0.1317 1.0000
8.000 0.5985 0.06702 0.06267 0.0212 0.1292 1.0000
8.250 0.5761 0.07176 0.06740 0.0195 0.1273 1.0000
8.500 0.5919 0.07560 0.07120 0.0227 0.1185 1.0000
8.750 0.5677 0.08107 0.07665 0.0185 0.1182 1.0000
9.000 0.5453 0.08666 0.08217 0.0136 0.1164 1.0000
9.250 0.5370 0.09114 0.08661 0.0117 0.1114 1.0000
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Polar data table (+)
Polar graphs
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