ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.18 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor07-il-1000000.txt Download as CSV file: xf-hor07-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4504 0.10483 0.10327 0.0017 1.0000 0.0119
-8.500 -0.4451 0.10097 0.09942 -0.0003 1.0000 0.0120
-8.250 -0.4450 0.09646 0.09494 -0.0015 1.0000 0.0124
-8.000 -0.4370 0.09380 0.09229 -0.0026 1.0000 0.0125
-7.750 -0.4297 0.09108 0.08958 -0.0039 1.0000 0.0128
-7.500 -0.4229 0.08817 0.08670 -0.0056 1.0000 0.0130
-7.250 -0.4092 0.08470 0.08310 -0.0094 0.9148 0.0134
-7.000 -0.3997 0.08148 0.07966 -0.0121 0.8572 0.0138
-6.750 -0.3850 0.07755 0.07561 -0.0166 0.8288 0.0143
-6.500 -0.3623 0.07157 0.06952 -0.0254 0.8069 0.0156
-6.000 -0.2629 0.02071 0.01700 -0.0834 0.7900 0.0123
-5.750 -0.2301 0.01705 0.01271 -0.0861 0.7749 0.0125
-5.250 -0.1699 0.01446 0.00957 -0.0879 0.7494 0.0131
-5.000 -0.1399 0.01357 0.00848 -0.0885 0.7394 0.0133
-4.750 -0.1099 0.01275 0.00745 -0.0890 0.7298 0.0135
-4.500 -0.0800 0.01203 0.00657 -0.0895 0.7215 0.0137
-4.250 -0.0501 0.01140 0.00579 -0.0899 0.7137 0.0140
-4.000 -0.0203 0.01093 0.00520 -0.0902 0.7062 0.0144
-3.750 0.0093 0.01055 0.00472 -0.0905 0.6987 0.0149
-3.500 0.0391 0.01013 0.00420 -0.0908 0.6903 0.0154
-3.250 0.0687 0.00981 0.00380 -0.0910 0.6830 0.0158
-3.000 0.0989 0.00930 0.00317 -0.0914 0.6742 0.0175
-2.750 0.1283 0.00910 0.00292 -0.0916 0.6661 0.0194
-2.500 0.1578 0.00887 0.00263 -0.0918 0.6567 0.0227
-2.250 0.1873 0.00864 0.00241 -0.0920 0.6474 0.0320
-2.000 0.2165 0.00851 0.00225 -0.0922 0.6383 0.0416
-1.750 0.2457 0.00836 0.00211 -0.0924 0.6290 0.0546
-1.500 0.2750 0.00815 0.00201 -0.0927 0.6203 0.0928
-1.250 0.3041 0.00809 0.00195 -0.0929 0.6113 0.1156
-1.000 0.3331 0.00802 0.00193 -0.0931 0.6027 0.1356
-0.750 0.3621 0.00800 0.00189 -0.0932 0.5942 0.1498
-0.500 0.3911 0.00797 0.00186 -0.0934 0.5847 0.1619
-0.250 0.4201 0.00795 0.00184 -0.0935 0.5756 0.1772
0.000 0.4490 0.00794 0.00184 -0.0937 0.5659 0.1958
0.250 0.4780 0.00792 0.00184 -0.0938 0.5554 0.2159
0.500 0.5069 0.00791 0.00185 -0.0940 0.5441 0.2371
0.750 0.5358 0.00791 0.00187 -0.0942 0.5317 0.2629
1.000 0.5647 0.00790 0.00191 -0.0944 0.5184 0.2949
1.250 0.5936 0.00791 0.00194 -0.0946 0.5045 0.3278
1.500 0.6226 0.00786 0.00201 -0.0949 0.4904 0.3998
1.750 0.6518 0.00766 0.00211 -0.0953 0.4761 0.5484
2.000 0.6742 0.00670 0.00208 -0.0941 0.4605 1.0000
2.250 0.7028 0.00686 0.00215 -0.0943 0.4434 1.0000
2.500 0.7314 0.00704 0.00224 -0.0944 0.4249 1.0000
2.750 0.7599 0.00722 0.00234 -0.0945 0.4074 1.0000
3.000 0.7882 0.00745 0.00245 -0.0947 0.3817 1.0000
3.250 0.8164 0.00774 0.00258 -0.0948 0.3496 1.0000
3.500 0.8446 0.00800 0.00272 -0.0949 0.3286 1.0000
3.750 0.8728 0.00822 0.00288 -0.0951 0.3121 1.0000
4.000 0.9008 0.00850 0.00305 -0.0952 0.2876 1.0000
4.250 0.9272 0.00936 0.00346 -0.0954 0.1907 1.0000
4.500 0.9548 0.00974 0.00374 -0.0955 0.1740 1.0000
4.750 0.9820 0.01022 0.00406 -0.0956 0.1354 1.0000
5.000 1.0083 0.01099 0.00455 -0.0957 0.0728 1.0000
5.250 1.0350 0.01158 0.00497 -0.0956 0.0421 1.0000
5.500 1.0620 0.01201 0.00535 -0.0956 0.0340 1.0000
5.750 1.0893 0.01233 0.00571 -0.0955 0.0321 1.0000
6.000 1.1164 0.01264 0.00604 -0.0955 0.0307 1.0000
6.250 1.1433 0.01298 0.00640 -0.0954 0.0292 1.0000
6.500 1.1699 0.01338 0.00682 -0.0953 0.0281 1.0000
6.750 1.1961 0.01384 0.00732 -0.0951 0.0269 1.0000
7.000 1.2214 0.01445 0.00800 -0.0948 0.0256 1.0000
7.250 1.2458 0.01521 0.00885 -0.0945 0.0246 1.0000
7.500 1.2718 0.01555 0.00921 -0.0943 0.0243 1.0000
7.750 1.2977 0.01587 0.00957 -0.0941 0.0238 1.0000
8.000 1.3231 0.01627 0.01001 -0.0939 0.0231 1.0000
8.250 1.3479 0.01673 0.01051 -0.0936 0.0225 1.0000
8.500 1.3727 0.01716 0.01097 -0.0933 0.0217 1.0000
8.750 1.3972 0.01760 0.01144 -0.0929 0.0209 1.0000
9.000 1.4210 0.01813 0.01198 -0.0925 0.0200 1.0000
9.250 1.4393 0.01939 0.01335 -0.0914 0.0185 1.0000
9.500 1.4644 0.01962 0.01361 -0.0911 0.0180 1.0000
9.750 1.4907 0.01966 0.01366 -0.0911 0.0172 1.0000
10.000 1.5162 0.01980 0.01382 -0.0909 0.0160 1.0000
10.250 1.5412 0.01997 0.01395 -0.0907 0.0147 1.0000
10.500 1.5638 0.02045 0.01444 -0.0902 0.0131 1.0000
10.750 1.5888 0.02061 0.01459 -0.0899 0.0112 1.0000
11.000 1.6098 0.02121 0.01518 -0.0891 0.0095 1.0000
11.250 1.6297 0.02190 0.01591 -0.0882 0.0085 1.0000
11.500 1.6476 0.02273 0.01676 -0.0870 0.0077 1.0000
11.750 1.6615 0.02390 0.01802 -0.0853 0.0071 1.0000
12.000 1.6759 0.02486 0.01908 -0.0836 0.0069 1.0000
12.250 1.6878 0.02591 0.02023 -0.0816 0.0066 1.0000
12.500 1.6971 0.02705 0.02147 -0.0793 0.0064 1.0000
12.750 1.7013 0.02831 0.02283 -0.0763 0.0062 1.0000
13.000 1.7029 0.02984 0.02447 -0.0734 0.0061 1.0000
13.250 1.7050 0.03164 0.02637 -0.0712 0.0059 1.0000
13.500 1.7070 0.03372 0.02858 -0.0696 0.0058 1.0000
13.750 1.7077 0.03613 0.03110 -0.0684 0.0056 1.0000
14.000 1.7063 0.03898 0.03407 -0.0676 0.0054 1.0000
14.250 1.7014 0.04238 0.03761 -0.0670 0.0053 1.0000
14.500 1.6926 0.04638 0.04177 -0.0666 0.0051 1.0000
14.750 1.6815 0.05076 0.04632 -0.0664 0.0050 1.0000
15.000 1.6733 0.05490 0.05061 -0.0664 0.0050 1.0000
15.250 1.6675 0.05880 0.05464 -0.0667 0.0049 1.0000
15.500 1.6597 0.06304 0.05901 -0.0671 0.0049 1.0000
15.750 1.6509 0.06752 0.06363 -0.0677 0.0049 1.0000
16.000 1.6405 0.07235 0.06860 -0.0686 0.0048 1.0000
16.250 1.6293 0.07753 0.07392 -0.0698 0.0048 1.0000
16.500 1.6172 0.08307 0.07960 -0.0714 0.0048 1.0000
16.750 1.6042 0.08895 0.08562 -0.0732 0.0048 1.0000
17.000 1.5896 0.09522 0.09204 -0.0754 0.0047 1.0000
17.250 1.5747 0.10174 0.09870 -0.0778 0.0047 1.0000
17.500 1.5584 0.10868 0.10578 -0.0806 0.0047 1.0000
17.750 1.5415 0.11585 0.11309 -0.0836 0.0047 1.0000
18.000 1.5231 0.12355 0.12094 -0.0871 0.0047 1.0000
18.250 1.5048 0.13149 0.12902 -0.0910 0.0047 1.0000
18.500 1.4865 0.13962 0.13728 -0.0952 0.0047 1.0000
18.750 1.4660 0.14859 0.14640 -0.1001 0.0047 1.0000
19.000 1.4447 0.15827 0.15622 -0.1058 0.0047 1.0000
19.250 1.4228 0.16864 0.16674 -0.1121 0.0048 1.0000
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