ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 500,000 Max Cl/Cd: 80.52 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor07-il-500000-n5.txt Download as CSV file: xf-hor07-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR07 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3392 0.08058 0.07765 -0.0128 0.7168 0.0117
-7.750 -0.3365 0.07681 0.07385 -0.0139 0.7098 0.0115
-7.500 -0.4266 0.08730 0.08428 -0.0068 0.7238 0.0115
-7.250 -0.4158 0.08345 0.08040 -0.0105 0.7149 0.0113
-7.000 -0.4029 0.07910 0.07601 -0.0152 0.7071 0.0112
-6.750 -0.3871 0.07415 0.07102 -0.0210 0.6997 0.0111
-6.500 -0.3677 0.06846 0.06527 -0.0282 0.6921 0.0111
-6.000 -0.2657 0.02337 0.01862 -0.0819 0.6845 0.0112
-5.750 -0.2328 0.02007 0.01469 -0.0847 0.6710 0.0114
-5.500 -0.2015 0.01799 0.01212 -0.0863 0.6556 0.0114
-5.250 -0.1709 0.01654 0.01029 -0.0873 0.6408 0.0114
-5.000 -0.1407 0.01544 0.00889 -0.0880 0.6279 0.0115
-4.750 -0.1107 0.01458 0.00777 -0.0885 0.6153 0.0116
-4.500 -0.0809 0.01390 0.00686 -0.0890 0.6007 0.0118
-4.250 -0.0511 0.01327 0.00606 -0.0894 0.5894 0.0120
-4.000 -0.0211 0.01260 0.00524 -0.0899 0.5796 0.0125
-3.750 0.0084 0.01221 0.00474 -0.0903 0.5707 0.0131
-3.500 0.0379 0.01191 0.00433 -0.0906 0.5595 0.0138
-3.250 0.0672 0.01164 0.00395 -0.0908 0.5480 0.0146
-3.000 0.0966 0.01142 0.00362 -0.0910 0.5345 0.0156
-2.750 0.1260 0.01120 0.00329 -0.0913 0.5207 0.0171
-2.500 0.1551 0.01104 0.00305 -0.0915 0.5049 0.0206
-2.250 0.1843 0.01089 0.00284 -0.0917 0.4870 0.0276
-2.000 0.2134 0.01080 0.00267 -0.0920 0.4678 0.0366
-1.750 0.2425 0.01072 0.00253 -0.0922 0.4513 0.0459
-1.500 0.2715 0.01061 0.00240 -0.0924 0.4397 0.0615
-1.250 0.3006 0.01047 0.00234 -0.0927 0.4314 0.0960
-0.750 0.3585 0.01037 0.00227 -0.0931 0.4176 0.1356
-0.500 0.3874 0.01035 0.00225 -0.0932 0.4107 0.1505
-0.250 0.4162 0.01034 0.00224 -0.0934 0.4037 0.1656
0.000 0.4451 0.01032 0.00224 -0.0935 0.3974 0.1815
0.250 0.4739 0.01032 0.00225 -0.0937 0.3908 0.1956
0.500 0.5027 0.01032 0.00227 -0.0938 0.3851 0.2157
0.750 0.5315 0.01032 0.00231 -0.0940 0.3784 0.2367
1.000 0.5603 0.01034 0.00235 -0.0941 0.3723 0.2543
1.250 0.5890 0.01034 0.00240 -0.0943 0.3664 0.2759
1.500 0.6177 0.01036 0.00246 -0.0945 0.3600 0.3042
1.750 0.6464 0.01037 0.00253 -0.0946 0.3542 0.3327
2.250 0.7038 0.01033 0.00272 -0.0951 0.3430 0.4296
2.500 0.7254 0.00915 0.00274 -0.0937 0.3386 1.0000
2.750 0.7537 0.00936 0.00287 -0.0938 0.3241 1.0000
3.000 0.7815 0.00973 0.00305 -0.0939 0.2903 1.0000
3.250 0.8078 0.01064 0.00344 -0.0942 0.1880 1.0000
3.500 0.8355 0.01099 0.00370 -0.0942 0.1767 1.0000
3.750 0.8634 0.01124 0.00393 -0.0943 0.1721 1.0000
4.000 0.8913 0.01144 0.00414 -0.0944 0.1660 1.0000
4.250 0.9192 0.01166 0.00430 -0.0944 0.1427 1.0000
4.500 0.9465 0.01206 0.00463 -0.0944 0.1304 1.0000
4.750 0.9730 0.01265 0.00503 -0.0945 0.0749 1.0000
5.000 0.9997 0.01314 0.00542 -0.0944 0.0530 1.0000
5.250 1.0265 0.01354 0.00577 -0.0944 0.0411 1.0000
5.500 1.0533 0.01393 0.00613 -0.0943 0.0343 1.0000
5.750 1.0801 0.01430 0.00652 -0.0942 0.0310 1.0000
6.000 1.1067 0.01467 0.00692 -0.0941 0.0294 1.0000
6.250 1.1330 0.01507 0.00734 -0.0940 0.0281 1.0000
6.500 1.1591 0.01550 0.00780 -0.0938 0.0270 1.0000
6.750 1.1848 0.01598 0.00833 -0.0936 0.0260 1.0000
7.000 1.2100 0.01652 0.00893 -0.0933 0.0251 1.0000
7.250 1.2343 0.01719 0.00967 -0.0929 0.0242 1.0000
7.500 1.2587 0.01778 0.01032 -0.0926 0.0234 1.0000
7.750 1.2836 0.01821 0.01081 -0.0923 0.0228 1.0000
8.000 1.3080 0.01870 0.01136 -0.0919 0.0220 1.0000
8.250 1.3320 0.01922 0.01195 -0.0915 0.0211 1.0000
8.500 1.3553 0.01980 0.01259 -0.0910 0.0204 1.0000
8.750 1.3781 0.02042 0.01328 -0.0904 0.0198 1.0000
9.000 1.4006 0.02101 0.01393 -0.0899 0.0190 1.0000
9.250 1.4220 0.02172 0.01467 -0.0892 0.0180 1.0000
9.500 1.4408 0.02270 0.01572 -0.0882 0.0171 1.0000
9.750 1.4636 0.02311 0.01621 -0.0876 0.0165 1.0000
10.000 1.4858 0.02357 0.01675 -0.0870 0.0155 1.0000
10.250 1.5074 0.02405 0.01731 -0.0863 0.0143 1.0000
10.500 1.5287 0.02453 0.01782 -0.0856 0.0131 1.0000
10.750 1.5477 0.02522 0.01854 -0.0846 0.0120 1.0000
11.000 1.5655 0.02596 0.01940 -0.0835 0.0105 1.0000
11.250 1.5831 0.02663 0.02010 -0.0823 0.0087 1.0000
11.500 1.5970 0.02755 0.02106 -0.0807 0.0079 1.0000
11.750 1.6080 0.02863 0.02219 -0.0787 0.0072 1.0000
12.000 1.6141 0.02987 0.02353 -0.0761 0.0067 1.0000
12.250 1.6173 0.03137 0.02513 -0.0734 0.0064 1.0000
12.500 1.6203 0.03314 0.02700 -0.0713 0.0061 1.0000
12.750 1.6234 0.03513 0.02913 -0.0697 0.0059 1.0000
13.000 1.6260 0.03736 0.03150 -0.0685 0.0058 1.0000
13.250 1.6281 0.03979 0.03407 -0.0676 0.0056 1.0000
13.500 1.6294 0.04243 0.03686 -0.0669 0.0055 1.0000
13.750 1.6296 0.04528 0.03986 -0.0664 0.0053 1.0000
14.000 1.6288 0.04833 0.04305 -0.0661 0.0052 1.0000
14.250 1.6267 0.05159 0.04645 -0.0659 0.0051 1.0000
14.500 1.6232 0.05508 0.05009 -0.0659 0.0050 1.0000
14.750 1.6187 0.05880 0.05395 -0.0660 0.0048 1.0000
15.000 1.6123 0.06282 0.05811 -0.0663 0.0047 1.0000
15.250 1.6045 0.06715 0.06261 -0.0669 0.0047 1.0000
15.500 1.5954 0.07177 0.06738 -0.0677 0.0046 1.0000
15.750 1.5850 0.07670 0.07245 -0.0687 0.0045 1.0000
16.000 1.5736 0.08207 0.07797 -0.0702 0.0045 1.0000
16.250 1.5617 0.08774 0.08380 -0.0719 0.0044 1.0000
16.500 1.5484 0.09379 0.09000 -0.0740 0.0044 1.0000
16.750 1.5342 0.10022 0.09659 -0.0765 0.0043 1.0000
17.000 1.5191 0.10698 0.10350 -0.0792 0.0043 1.0000
17.250 1.5034 0.11402 0.11070 -0.0823 0.0043 1.0000
17.500 1.4866 0.12148 0.11832 -0.0857 0.0043 1.0000
17.750 1.4695 0.12930 0.12629 -0.0896 0.0043 1.0000
18.000 1.4517 0.13751 0.13465 -0.0939 0.0043 1.0000
18.250 1.4325 0.14634 0.14364 -0.0988 0.0043 1.0000
18.500 1.4117 0.15616 0.15362 -0.1045 0.0043 1.0000
18.750 1.3882 0.16735 0.16500 -0.1112 0.0044 1.0000
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