NACA 0008 (naca0008-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0008 (naca0008-il) Reynolds number: 100,000 Max Cl/Cd: 30.44 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0008-il-100000-n5.txt Download as CSV file: xf-naca0008-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7704 0.07881 0.07389 -0.0050 1.0000 0.0230
-10.000 -0.7872 0.07104 0.06603 -0.0120 1.0000 0.0229
-9.750 -0.8058 0.06521 0.06012 -0.0156 1.0000 0.0227
-9.500 -0.8228 0.06029 0.05499 -0.0164 1.0000 0.0227
-9.250 -0.8342 0.05521 0.04957 -0.0166 1.0000 0.0228
-9.000 -0.8399 0.05033 0.04424 -0.0161 1.0000 0.0230
-8.750 -0.8390 0.04604 0.03962 -0.0154 1.0000 0.0237
-8.500 -0.8278 0.04379 0.03718 -0.0148 1.0000 0.0250
-8.250 -0.8154 0.04131 0.03444 -0.0140 1.0000 0.0265
-8.000 -0.8032 0.03803 0.03069 -0.0129 1.0000 0.0279
-7.750 -0.7886 0.03468 0.02681 -0.0117 1.0000 0.0292
-7.500 -0.7707 0.03193 0.02349 -0.0105 1.0000 0.0314
-7.250 -0.7514 0.02954 0.02077 -0.0096 1.0000 0.0341
-7.000 -0.7302 0.02782 0.01891 -0.0089 1.0000 0.0367
-6.750 -0.7078 0.02621 0.01703 -0.0080 1.0000 0.0403
-6.500 -0.6849 0.02464 0.01514 -0.0072 1.0000 0.0444
-6.250 -0.6625 0.02322 0.01369 -0.0065 1.0000 0.0481
-6.000 -0.6389 0.02225 0.01256 -0.0058 1.0000 0.0536
-5.750 -0.6161 0.02102 0.01123 -0.0049 1.0000 0.0575
-5.500 -0.5932 0.02010 0.01029 -0.0042 1.0000 0.0630
-5.250 -0.5696 0.01930 0.00933 -0.0034 1.0000 0.0687
-5.000 -0.5474 0.01832 0.00834 -0.0025 1.0000 0.0740
-4.750 -0.5241 0.01757 0.00750 -0.0016 1.0000 0.0819
-4.500 -0.5011 0.01677 0.00673 -0.0008 1.0000 0.0950
-4.250 -0.4783 0.01596 0.00606 -0.0001 1.0000 0.1217
-4.000 -0.4561 0.01507 0.00549 0.0007 1.0000 0.1823
-3.750 -0.4340 0.01426 0.00505 0.0014 1.0000 0.2623
-3.500 -0.4115 0.01362 0.00471 0.0022 1.0000 0.3378
-3.250 -0.3902 0.01294 0.00447 0.0034 1.0000 0.4369
-3.000 -0.3696 0.01232 0.00432 0.0050 1.0000 0.5449
-2.750 -0.3480 0.01188 0.00423 0.0066 1.0000 0.6302
-2.500 -0.3249 0.01159 0.00416 0.0082 1.0000 0.6980
-2.250 -0.3017 0.01141 0.00411 0.0098 1.0000 0.7607
-2.000 -0.2765 0.01131 0.00412 0.0112 1.0000 0.8156
-1.750 -0.2477 0.01129 0.00412 0.0117 1.0000 0.8626
-1.500 -0.2131 0.01131 0.00410 0.0108 1.0000 0.9016
-1.250 -0.1747 0.01135 0.00408 0.0090 1.0000 0.9340
-1.000 -0.1318 0.01137 0.00402 0.0059 1.0000 0.9592
-0.750 -0.0864 0.01136 0.00395 0.0022 1.0000 0.9793
-0.500 -0.0385 0.01132 0.00387 -0.0022 1.0000 0.9954
-0.250 -0.0137 0.01126 0.00379 -0.0022 1.0000 1.0000
0.000 0.0000 0.01124 0.00377 0.0000 1.0000 1.0000
0.250 0.0137 0.01126 0.00379 0.0022 1.0000 1.0000
0.500 0.0386 0.01132 0.00387 0.0022 0.9954 1.0000
0.750 0.0864 0.01136 0.00395 -0.0022 0.9793 1.0000
1.000 0.1318 0.01137 0.00402 -0.0059 0.9592 1.0000
1.250 0.1747 0.01135 0.00408 -0.0090 0.9340 1.0000
1.500 0.2131 0.01131 0.00410 -0.0108 0.9016 1.0000
1.750 0.2477 0.01129 0.00412 -0.0117 0.8626 1.0000
2.000 0.2765 0.01131 0.00412 -0.0112 0.8156 1.0000
2.250 0.3017 0.01141 0.00411 -0.0098 0.7607 1.0000
2.500 0.3249 0.01159 0.00416 -0.0082 0.6980 1.0000
2.750 0.3480 0.01188 0.00423 -0.0066 0.6301 1.0000
3.000 0.3696 0.01232 0.00432 -0.0050 0.5449 1.0000
3.250 0.3902 0.01294 0.00447 -0.0034 0.4369 1.0000
3.500 0.4115 0.01362 0.00471 -0.0023 0.3377 1.0000
3.750 0.4341 0.01426 0.00505 -0.0014 0.2623 1.0000
4.000 0.4561 0.01507 0.00549 -0.0007 0.1823 1.0000
4.250 0.4783 0.01596 0.00606 0.0001 0.1217 1.0000
4.500 0.5011 0.01677 0.00673 0.0008 0.0950 1.0000
4.750 0.5241 0.01757 0.00750 0.0016 0.0819 1.0000
5.000 0.5474 0.01832 0.00834 0.0025 0.0740 1.0000
5.250 0.5696 0.01930 0.00933 0.0034 0.0688 1.0000
5.500 0.5932 0.02010 0.01029 0.0042 0.0630 1.0000
5.750 0.6161 0.02102 0.01123 0.0049 0.0575 1.0000
6.000 0.6389 0.02225 0.01256 0.0058 0.0536 1.0000
6.250 0.6625 0.02321 0.01369 0.0065 0.0480 1.0000
6.500 0.6849 0.02464 0.01514 0.0072 0.0444 1.0000
6.750 0.7078 0.02621 0.01703 0.0080 0.0403 1.0000
7.000 0.7302 0.02782 0.01891 0.0089 0.0367 1.0000
7.250 0.7514 0.02954 0.02077 0.0096 0.0341 1.0000
7.500 0.7707 0.03193 0.02349 0.0105 0.0314 1.0000
7.750 0.7886 0.03468 0.02681 0.0117 0.0292 1.0000
8.000 0.8032 0.03803 0.03069 0.0129 0.0279 1.0000
8.250 0.8154 0.04131 0.03443 0.0140 0.0265 1.0000
8.500 0.8278 0.04378 0.03717 0.0148 0.0250 1.0000
8.750 0.8390 0.04603 0.03962 0.0154 0.0237 1.0000
9.000 0.8399 0.05034 0.04424 0.0161 0.0230 1.0000
9.250 0.8342 0.05522 0.04958 0.0166 0.0227 1.0000
9.500 0.8228 0.06031 0.05500 0.0164 0.0227 1.0000
9.750 0.8059 0.06524 0.06016 0.0156 0.0227 1.0000
10.000 0.7875 0.07108 0.06613 0.0119 0.0229 1.0000
10.250 0.7706 0.07890 0.07398 0.0049 0.0230 1.0000
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Polar data table (+)
Polar graphs
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