NACA 0008 (naca0008-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0008 (naca0008-il) Reynolds number: 500,000 Max Cl/Cd: 56.21 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0008-il-500000-n5.txt Download as CSV file: xf-naca0008-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -1.0353 0.07502 0.07264 0.0049 1.0000 0.0050
-13.000 -1.0853 0.05629 0.05354 -0.0104 1.0000 0.0048
-12.750 -1.1054 0.04814 0.04513 -0.0176 1.0000 0.0048
-12.500 -1.1217 0.04299 0.03975 -0.0202 1.0000 0.0048
-12.250 -1.1347 0.03937 0.03591 -0.0196 1.0000 0.0048
-12.000 -1.1413 0.03658 0.03291 -0.0177 1.0000 0.0049
-11.750 -1.1383 0.03417 0.03029 -0.0164 1.0000 0.0050
-11.500 -1.1301 0.03213 0.02804 -0.0152 1.0000 0.0051
-11.250 -1.1185 0.03033 0.02605 -0.0141 1.0000 0.0052
-11.000 -1.1046 0.02869 0.02422 -0.0131 1.0000 0.0054
-10.750 -1.0892 0.02715 0.02249 -0.0122 1.0000 0.0056
-10.500 -1.0725 0.02568 0.02083 -0.0112 1.0000 0.0058
-10.250 -1.0545 0.02431 0.01926 -0.0104 1.0000 0.0060
-10.000 -1.0351 0.02310 0.01787 -0.0096 1.0000 0.0063
-9.750 -1.0146 0.02203 0.01658 -0.0088 1.0000 0.0067
-9.500 -0.9937 0.02096 0.01535 -0.0081 1.0000 0.0069
-9.250 -0.9743 0.01960 0.01384 -0.0072 1.0000 0.0074
-9.000 -0.9522 0.01872 0.01284 -0.0066 1.0000 0.0078
-8.750 -0.9293 0.01794 0.01196 -0.0060 1.0000 0.0083
-8.500 -0.9062 0.01718 0.01109 -0.0055 1.0000 0.0088
-8.250 -0.8828 0.01646 0.01026 -0.0049 1.0000 0.0094
-8.000 -0.8589 0.01581 0.00950 -0.0043 1.0000 0.0099
-7.750 -0.8357 0.01502 0.00861 -0.0037 1.0000 0.0113
-7.500 -0.8111 0.01453 0.00811 -0.0033 1.0000 0.0126
-7.250 -0.7863 0.01407 0.00759 -0.0029 1.0000 0.0140
-7.000 -0.7617 0.01355 0.00700 -0.0024 1.0000 0.0155
-6.750 -0.7366 0.01314 0.00660 -0.0019 1.0000 0.0183
-6.500 -0.7110 0.01286 0.00629 -0.0016 1.0000 0.0212
-6.250 -0.6852 0.01265 0.00602 -0.0012 1.0000 0.0229
-6.000 -0.6607 0.01215 0.00547 -0.0007 1.0000 0.0255
-5.750 -0.6356 0.01184 0.00515 -0.0003 1.0000 0.0280
-5.500 -0.6103 0.01157 0.00484 0.0002 1.0000 0.0302
-5.250 -0.5851 0.01131 0.00454 0.0007 1.0000 0.0318
-5.000 -0.5599 0.01107 0.00425 0.0012 1.0000 0.0329
-4.750 -0.5357 0.01065 0.00380 0.0019 1.0000 0.0361
-4.500 -0.5111 0.01035 0.00350 0.0025 1.0000 0.0390
-4.250 -0.4863 0.01010 0.00323 0.0031 1.0000 0.0418
-4.000 -0.4614 0.00987 0.00296 0.0037 1.0000 0.0447
-3.750 -0.4368 0.00960 0.00273 0.0043 1.0000 0.0521
-3.500 -0.4124 0.00933 0.00253 0.0050 1.0000 0.0668
-3.250 -0.3840 0.00901 0.00232 0.0047 0.9986 0.0932
-3.000 -0.3498 0.00867 0.00212 0.0030 0.9950 0.1290
-2.750 -0.3164 0.00832 0.00195 0.0016 0.9905 0.1722
-2.500 -0.2821 0.00797 0.00179 0.0000 0.9860 0.2212
-2.250 -0.2504 0.00758 0.00165 -0.0011 0.9789 0.2852
-2.000 -0.2183 0.00721 0.00153 -0.0022 0.9712 0.3514
-1.750 -0.1863 0.00684 0.00143 -0.0033 0.9618 0.4211
-1.500 -0.1557 0.00649 0.00134 -0.0039 0.9494 0.4936
-1.250 -0.1274 0.00614 0.00128 -0.0040 0.9333 0.5695
-1.000 -0.1006 0.00587 0.00122 -0.0036 0.9136 0.6354
-0.750 -0.0746 0.00570 0.00118 -0.0029 0.8907 0.6811
-0.500 -0.0493 0.00559 0.00114 -0.0021 0.8635 0.7209
-0.250 -0.0246 0.00552 0.00111 -0.0011 0.8318 0.7601
0.000 0.0000 0.00550 0.00110 0.0000 0.7969 0.7968
0.250 0.0246 0.00552 0.00111 0.0011 0.7602 0.8317
0.500 0.0493 0.00559 0.00114 0.0021 0.7210 0.8634
0.750 0.0745 0.00570 0.00118 0.0030 0.6807 0.8908
1.000 0.1006 0.00586 0.00122 0.0036 0.6355 0.9138
1.250 0.1274 0.00614 0.00128 0.0040 0.5701 0.9334
1.500 0.1557 0.00649 0.00134 0.0039 0.4936 0.9494
1.750 0.1863 0.00684 0.00143 0.0033 0.4212 0.9618
2.000 0.2183 0.00721 0.00153 0.0022 0.3517 0.9712
2.250 0.2504 0.00758 0.00165 0.0011 0.2852 0.9790
2.500 0.2821 0.00797 0.00179 0.0000 0.2212 0.9860
2.750 0.3165 0.00832 0.00195 -0.0016 0.1721 0.9905
3.000 0.3498 0.00867 0.00212 -0.0031 0.1289 0.9950
3.250 0.3841 0.00901 0.00232 -0.0047 0.0930 0.9986
3.500 0.4124 0.00933 0.00253 -0.0050 0.0669 1.0000
3.750 0.4369 0.00960 0.00273 -0.0044 0.0521 1.0000
4.000 0.4615 0.00987 0.00296 -0.0037 0.0448 1.0000
4.250 0.4863 0.01010 0.00323 -0.0031 0.0418 1.0000
4.500 0.5111 0.01035 0.00350 -0.0025 0.0390 1.0000
4.750 0.5357 0.01065 0.00380 -0.0019 0.0361 1.0000
5.000 0.5600 0.01107 0.00425 -0.0012 0.0329 1.0000
5.250 0.5851 0.01131 0.00453 -0.0007 0.0318 1.0000
5.500 0.6103 0.01157 0.00484 -0.0002 0.0302 1.0000
5.750 0.6356 0.01184 0.00515 0.0003 0.0280 1.0000
6.000 0.6607 0.01215 0.00547 0.0007 0.0254 1.0000
6.250 0.6852 0.01265 0.00602 0.0012 0.0229 1.0000
6.500 0.7110 0.01286 0.00629 0.0016 0.0212 1.0000
6.750 0.7366 0.01314 0.00660 0.0019 0.0183 1.0000
7.000 0.7617 0.01355 0.00700 0.0024 0.0155 1.0000
7.250 0.7862 0.01407 0.00759 0.0029 0.0140 1.0000
7.500 0.8110 0.01453 0.00811 0.0033 0.0126 1.0000
7.750 0.8357 0.01502 0.00861 0.0037 0.0113 1.0000
8.000 0.8589 0.01581 0.00950 0.0044 0.0099 1.0000
8.250 0.8827 0.01646 0.01026 0.0049 0.0094 1.0000
8.500 0.9062 0.01718 0.01109 0.0055 0.0088 1.0000
8.750 0.9293 0.01794 0.01196 0.0061 0.0083 1.0000
9.000 0.9521 0.01872 0.01285 0.0066 0.0078 1.0000
9.250 0.9743 0.01960 0.01384 0.0072 0.0074 1.0000
9.500 0.9937 0.02096 0.01535 0.0081 0.0069 1.0000
9.750 1.0146 0.02202 0.01658 0.0088 0.0067 1.0000
10.000 1.0351 0.02310 0.01787 0.0096 0.0063 1.0000
10.250 1.0545 0.02430 0.01925 0.0104 0.0060 1.0000
10.500 1.0724 0.02568 0.02082 0.0112 0.0058 1.0000
10.750 1.0892 0.02715 0.02249 0.0122 0.0056 1.0000
11.000 1.1046 0.02869 0.02422 0.0131 0.0054 1.0000
11.250 1.1185 0.03033 0.02605 0.0141 0.0052 1.0000
11.500 1.1301 0.03212 0.02803 0.0152 0.0051 1.0000
11.750 1.1384 0.03416 0.03027 0.0163 0.0050 1.0000
12.000 1.1414 0.03659 0.03291 0.0177 0.0049 1.0000
12.250 1.1350 0.03937 0.03591 0.0195 0.0048 1.0000
12.500 1.1220 0.04300 0.03976 0.0201 0.0048 1.0000
12.750 1.1055 0.04820 0.04519 0.0175 0.0048 1.0000
13.000 1.0859 0.05633 0.05358 0.0102 0.0048 1.0000
13.250 1.0390 0.07435 0.07196 -0.0046 0.0050 1.0000
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