ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.38 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor07-il-1000000-n5.txt Download as CSV file: xf-hor07-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4522 0.10229 0.09810 0.0020 0.1790 0.0075
-8.250 -0.4474 0.09847 0.09429 0.0000 0.1786 0.0077
-8.000 -0.4431 0.09463 0.09046 -0.0021 0.1783 0.0078
-7.000 -0.3772 0.02322 0.01769 -0.0824 0.1788 0.0082
-6.750 -0.3465 0.02088 0.01496 -0.0845 0.1783 0.0083
-6.500 -0.3163 0.01921 0.01298 -0.0859 0.1779 0.0083
-6.250 -0.2863 0.01792 0.01141 -0.0869 0.1771 0.0084
-6.000 -0.2568 0.01709 0.01039 -0.0876 0.1764 0.0084
-5.750 -0.2273 0.01639 0.00952 -0.0882 0.1760 0.0085
-5.500 -0.1976 0.01554 0.00846 -0.0888 0.1756 0.0086
-5.250 -0.1676 0.01468 0.00740 -0.0894 0.1753 0.0086
-5.000 -0.1377 0.01394 0.00649 -0.0900 0.1750 0.0087
-4.750 -0.1079 0.01334 0.00573 -0.0904 0.1747 0.0088
-4.500 -0.0782 0.01285 0.00512 -0.0908 0.1744 0.0090
-4.250 -0.0487 0.01246 0.00462 -0.0912 0.1742 0.0092
-4.000 -0.0193 0.01214 0.00422 -0.0914 0.1739 0.0095
-3.750 0.0100 0.01190 0.00391 -0.0917 0.1736 0.0100
-3.500 0.0393 0.01169 0.00365 -0.0919 0.1734 0.0104
-3.250 0.0685 0.01152 0.00341 -0.0921 0.1732 0.0108
-3.000 0.0976 0.01137 0.00320 -0.0923 0.1729 0.0113
-2.750 0.1267 0.01124 0.00303 -0.0924 0.1727 0.0118
-2.500 0.1559 0.01111 0.00286 -0.0926 0.1726 0.0129
-2.000 0.2140 0.01090 0.00262 -0.0930 0.1722 0.0200
-1.750 0.2431 0.01080 0.00254 -0.0931 0.1721 0.0274
-1.500 0.2721 0.01071 0.00246 -0.0933 0.1720 0.0374
-1.250 0.3011 0.01065 0.00240 -0.0935 0.1719 0.0455
-1.000 0.3301 0.01056 0.00235 -0.0937 0.1718 0.0625
-0.750 0.3591 0.01045 0.00233 -0.0939 0.1718 0.0956
-0.500 0.3879 0.01046 0.00232 -0.0940 0.1717 0.1038
-0.250 0.4169 0.01041 0.00233 -0.0942 0.1716 0.1205
0.000 0.4457 0.01039 0.00235 -0.0943 0.1715 0.1368
0.250 0.4745 0.01038 0.00237 -0.0945 0.1715 0.1523
0.500 0.5033 0.01039 0.00239 -0.0946 0.1714 0.1643
1.000 0.5607 0.01042 0.00247 -0.0949 0.1714 0.1898
1.250 0.5894 0.01042 0.00254 -0.0950 0.1714 0.2131
1.500 0.6181 0.01044 0.00259 -0.0952 0.1714 0.2307
1.750 0.6467 0.01047 0.00266 -0.0953 0.1714 0.2453
2.000 0.6753 0.01051 0.00274 -0.0954 0.1705 0.2621
2.250 0.7039 0.01057 0.00285 -0.0956 0.1671 0.2855
2.500 0.7324 0.01065 0.00297 -0.0957 0.1632 0.3130
2.750 0.7610 0.01062 0.00301 -0.0958 0.1595 0.3346
3.000 0.7895 0.01070 0.00310 -0.0960 0.1422 0.3905
3.250 0.8178 0.01083 0.00324 -0.0961 0.1373 0.4039
3.500 0.8460 0.01096 0.00343 -0.0963 0.1330 0.4174
3.750 0.8746 0.01092 0.00364 -0.0966 0.1289 0.5351
4.000 0.8968 0.01028 0.00382 -0.0956 0.0847 1.0000
4.250 0.9243 0.01066 0.00409 -0.0956 0.0610 1.0000
4.500 0.9518 0.01101 0.00435 -0.0957 0.0448 1.0000
4.750 0.9793 0.01132 0.00459 -0.0957 0.0329 1.0000
5.000 1.0068 0.01159 0.00482 -0.0957 0.0284 1.0000
5.250 1.0343 0.01187 0.00507 -0.0957 0.0252 1.0000
5.500 1.0617 0.01213 0.00535 -0.0957 0.0236 1.0000
5.750 1.0890 0.01239 0.00562 -0.0957 0.0231 1.0000
6.000 1.1162 0.01265 0.00591 -0.0957 0.0226 1.0000
6.250 1.1433 0.01294 0.00621 -0.0956 0.0220 1.0000
6.500 1.1701 0.01324 0.00655 -0.0956 0.0215 1.0000
6.750 1.1968 0.01355 0.00686 -0.0955 0.0205 1.0000
7.000 1.2232 0.01389 0.00720 -0.0954 0.0193 1.0000
7.250 1.2493 0.01428 0.00761 -0.0953 0.0183 1.0000
7.500 1.2750 0.01474 0.00812 -0.0951 0.0175 1.0000
7.750 1.3007 0.01516 0.00858 -0.0949 0.0171 1.0000
8.000 1.3265 0.01550 0.00894 -0.0947 0.0169 1.0000
8.250 1.3522 0.01583 0.00930 -0.0945 0.0166 1.0000
8.500 1.3777 0.01616 0.00966 -0.0943 0.0161 1.0000
8.750 1.4031 0.01649 0.01004 -0.0941 0.0153 1.0000
9.000 1.4282 0.01684 0.01040 -0.0939 0.0144 1.0000
9.250 1.4529 0.01722 0.01078 -0.0936 0.0133 1.0000
9.500 1.4768 0.01769 0.01126 -0.0932 0.0123 1.0000
9.750 1.5011 0.01809 0.01170 -0.0928 0.0116 1.0000
10.000 1.5248 0.01852 0.01216 -0.0924 0.0087 1.0000
10.250 1.5465 0.01919 0.01277 -0.0918 0.0064 1.0000
10.500 1.5679 0.01985 0.01348 -0.0911 0.0056 1.0000
10.750 1.5884 0.02058 0.01427 -0.0902 0.0052 1.0000
11.000 1.6079 0.02136 0.01512 -0.0892 0.0048 1.0000
11.250 1.6264 0.02219 0.01602 -0.0881 0.0045 1.0000
11.500 1.6436 0.02308 0.01700 -0.0868 0.0041 1.0000
11.750 1.6603 0.02394 0.01794 -0.0855 0.0039 1.0000
12.000 1.6758 0.02480 0.01888 -0.0840 0.0038 1.0000
12.250 1.6893 0.02572 0.01989 -0.0822 0.0037 1.0000
12.500 1.7005 0.02673 0.02099 -0.0801 0.0037 1.0000
12.750 1.7079 0.02785 0.02221 -0.0776 0.0036 1.0000
13.000 1.7108 0.02918 0.02364 -0.0746 0.0035 1.0000
13.250 1.7145 0.03073 0.02530 -0.0723 0.0034 1.0000
13.500 1.7181 0.03252 0.02720 -0.0706 0.0033 1.0000
13.750 1.7216 0.03454 0.02932 -0.0693 0.0033 1.0000
14.000 1.7244 0.03678 0.03169 -0.0683 0.0032 1.0000
14.250 1.7265 0.03924 0.03426 -0.0675 0.0031 1.0000
14.500 1.7275 0.04192 0.03706 -0.0670 0.0031 1.0000
14.750 1.7273 0.04481 0.04006 -0.0666 0.0030 1.0000
15.000 1.7257 0.04795 0.04332 -0.0663 0.0030 1.0000
15.250 1.7223 0.05132 0.04681 -0.0662 0.0029 1.0000
15.500 1.7175 0.05498 0.05059 -0.0662 0.0029 1.0000
15.750 1.7114 0.05887 0.05461 -0.0665 0.0028 1.0000
16.000 1.7033 0.06308 0.05895 -0.0669 0.0028 1.0000
16.250 1.6941 0.06757 0.06357 -0.0675 0.0028 1.0000
16.500 1.6836 0.07240 0.06852 -0.0684 0.0027 1.0000
16.750 1.6720 0.07759 0.07384 -0.0696 0.0027 1.0000
17.000 1.6597 0.08311 0.07950 -0.0712 0.0027 1.0000
17.250 1.6465 0.08897 0.08550 -0.0730 0.0027 1.0000
17.500 1.6316 0.09523 0.09189 -0.0752 0.0026 1.0000
17.750 1.6162 0.10174 0.09853 -0.0776 0.0026 1.0000
18.000 1.5997 0.10862 0.10555 -0.0803 0.0026 1.0000
18.250 1.5816 0.11593 0.11300 -0.0835 0.0026 1.0000
18.500 1.5629 0.12357 0.12078 -0.0869 0.0026 1.0000
18.750 1.5441 0.13147 0.12882 -0.0908 0.0026 1.0000
19.000 1.5246 0.13974 0.13722 -0.0951 0.0026 1.0000
19.250 1.5033 0.14871 0.14634 -0.1000 0.0026 1.0000
|
Polar data table (+)
Polar graphs
<< Back to ONERA HOR07 AIRFOIL (hor07-il)