ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 500,000 Max Cl/Cd: 98 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor07-il-500000.txt Download as CSV file: xf-hor07-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4271 0.10118 0.09901 -0.0007 1.0000 0.0199
-8.000 -0.4242 0.09747 0.09533 -0.0053 1.0000 0.0207
-7.750 -0.4192 0.09394 0.09183 -0.0083 1.0000 0.0208
-7.500 -0.4090 0.09006 0.08797 -0.0122 1.0000 0.0209
-7.250 -0.3959 0.08583 0.08375 -0.0170 1.0000 0.0210
-7.000 -0.3913 0.08072 0.07866 -0.0188 1.0000 0.0216
-6.750 -0.3772 0.07807 0.07603 -0.0202 1.0000 0.0221
-6.500 -0.3609 0.07493 0.07289 -0.0233 1.0000 0.0226
-6.250 -0.3423 0.07128 0.06926 -0.0276 1.0000 0.0232
-6.000 -0.3108 0.06648 0.06441 -0.0359 0.9638 0.0243
-5.750 -0.2810 0.06132 0.05912 -0.0438 0.9153 0.0258
-5.500 -0.2392 0.05454 0.05209 -0.0555 0.8776 0.0274
-5.250 -0.2057 0.04389 0.04116 -0.0673 0.8561 0.0283
-5.000 -0.1827 0.04191 0.03903 -0.0687 0.8353 0.0291
-4.750 -0.1161 0.02170 0.01715 -0.0865 0.8267 0.0211
-4.500 -0.0834 0.01780 0.01267 -0.0887 0.8107 0.0203
-4.250 -0.0532 0.01674 0.01125 -0.0892 0.7950 0.0208
-4.000 -0.0224 0.01521 0.00933 -0.0900 0.7819 0.0211
-3.750 0.0081 0.01383 0.00765 -0.0905 0.7705 0.0212
-3.500 0.0388 0.01243 0.00600 -0.0911 0.7603 0.0219
-3.250 0.0686 0.01178 0.00526 -0.0915 0.7504 0.0231
-3.000 0.0981 0.01137 0.00474 -0.0917 0.7412 0.0249
-2.750 0.1276 0.01105 0.00431 -0.0918 0.7321 0.0271
-2.500 0.1577 0.01050 0.00370 -0.0922 0.7234 0.0323
-2.250 0.1872 0.01018 0.00331 -0.0924 0.7153 0.0432
-2.000 0.2169 0.00987 0.00299 -0.0927 0.7068 0.0577
-1.750 0.2462 0.00959 0.00281 -0.0930 0.6993 0.0957
-1.500 0.2753 0.00945 0.00278 -0.0932 0.6912 0.1338
-1.250 0.3041 0.00942 0.00272 -0.0933 0.6836 0.1535
-1.000 0.3331 0.00935 0.00266 -0.0934 0.6753 0.1680
-0.750 0.3620 0.00931 0.00261 -0.0935 0.6676 0.1835
-0.500 0.3910 0.00926 0.00256 -0.0936 0.6590 0.1999
-0.250 0.4199 0.00922 0.00252 -0.0938 0.6505 0.2184
0.000 0.4487 0.00916 0.00250 -0.0939 0.6416 0.2406
0.250 0.4777 0.00908 0.00248 -0.0941 0.6322 0.2680
0.500 0.5066 0.00903 0.00248 -0.0942 0.6228 0.3007
0.750 0.5356 0.00893 0.00247 -0.0944 0.6129 0.3419
1.000 0.5647 0.00870 0.00254 -0.0948 0.6030 0.4490
1.250 0.5861 0.00743 0.00242 -0.0933 0.5940 1.0000
1.500 0.6149 0.00752 0.00243 -0.0934 0.5833 1.0000
1.750 0.6436 0.00762 0.00247 -0.0935 0.5723 1.0000
2.000 0.6723 0.00773 0.00252 -0.0935 0.5615 1.0000
2.250 0.7009 0.00785 0.00257 -0.0936 0.5504 1.0000
2.500 0.7295 0.00797 0.00264 -0.0937 0.5376 1.0000
2.750 0.7579 0.00810 0.00271 -0.0937 0.5216 1.0000
3.000 0.7863 0.00825 0.00280 -0.0938 0.5028 1.0000
3.250 0.8144 0.00845 0.00290 -0.0938 0.4800 1.0000
3.500 0.8423 0.00870 0.00302 -0.0939 0.4548 1.0000
3.750 0.8703 0.00895 0.00319 -0.0940 0.4341 1.0000
4.000 0.8983 0.00917 0.00335 -0.0940 0.4150 1.0000
4.250 0.9261 0.00945 0.00353 -0.0941 0.3899 1.0000
4.500 0.9538 0.00974 0.00372 -0.0941 0.3627 1.0000
4.750 0.9810 0.01014 0.00398 -0.0942 0.3282 1.0000
5.000 1.0078 0.01065 0.00430 -0.0943 0.2832 1.0000
5.250 1.0311 0.01218 0.00513 -0.0943 0.1422 1.0000
5.500 1.0546 0.01360 0.00606 -0.0942 0.0572 1.0000
5.750 1.0807 0.01421 0.00665 -0.0940 0.0464 1.0000
6.000 1.1065 0.01484 0.00732 -0.0937 0.0421 1.0000
6.250 1.1326 0.01533 0.00787 -0.0935 0.0402 1.0000
6.500 1.1582 0.01587 0.00846 -0.0932 0.0384 1.0000
6.750 1.1833 0.01647 0.00911 -0.0929 0.0367 1.0000
7.000 1.2075 0.01721 0.00990 -0.0925 0.0354 1.0000
7.250 1.2300 0.01817 0.01094 -0.0918 0.0343 1.0000
7.500 1.2498 0.01951 0.01239 -0.0908 0.0333 1.0000
7.750 1.2715 0.02047 0.01343 -0.0900 0.0326 1.0000
8.000 1.2953 0.02098 0.01401 -0.0895 0.0318 1.0000
8.250 1.3187 0.02152 0.01461 -0.0890 0.0305 1.0000
8.500 1.3414 0.02213 0.01527 -0.0884 0.0291 1.0000
8.750 1.3635 0.02275 0.01594 -0.0877 0.0277 1.0000
9.000 1.3836 0.02361 0.01683 -0.0869 0.0263 1.0000
9.250 1.3946 0.02603 0.01935 -0.0848 0.0247 1.0000
9.500 1.4173 0.02628 0.01970 -0.0841 0.0239 1.0000
9.750 1.4380 0.02682 0.02033 -0.0833 0.0226 1.0000
10.000 1.4578 0.02735 0.02093 -0.0824 0.0210 1.0000
10.250 1.4756 0.02802 0.02162 -0.0814 0.0196 1.0000
10.500 1.4847 0.02986 0.02359 -0.0791 0.0178 1.0000
10.750 1.5019 0.03033 0.02416 -0.0779 0.0163 1.0000
11.000 1.5172 0.03086 0.02474 -0.0765 0.0151 1.0000
11.250 1.5271 0.03171 0.02561 -0.0745 0.0142 1.0000
11.500 1.5235 0.03406 0.02808 -0.0710 0.0134 1.0000
11.750 1.5313 0.03545 0.02962 -0.0692 0.0128 1.0000
12.000 1.5370 0.03722 0.03155 -0.0676 0.0122 1.0000
12.250 1.5421 0.03915 0.03362 -0.0663 0.0117 1.0000
12.500 1.5478 0.04110 0.03568 -0.0653 0.0112 1.0000
12.750 1.5529 0.04318 0.03785 -0.0647 0.0109 1.0000
13.000 1.5570 0.04549 0.04024 -0.0642 0.0106 1.0000
13.250 1.5570 0.04837 0.04323 -0.0637 0.0103 1.0000
13.500 1.5491 0.05230 0.04733 -0.0630 0.0100 1.0000
13.750 1.5411 0.05640 0.05162 -0.0624 0.0098 1.0000
14.000 1.5361 0.06018 0.05560 -0.0623 0.0097 1.0000
14.250 1.5288 0.06438 0.06001 -0.0625 0.0096 1.0000
14.500 1.5192 0.06900 0.06482 -0.0629 0.0095 1.0000
14.750 1.5068 0.07415 0.07018 -0.0637 0.0094 1.0000
15.000 1.4931 0.07968 0.07591 -0.0650 0.0093 1.0000
15.250 1.4771 0.08583 0.08227 -0.0668 0.0092 1.0000
15.500 1.4593 0.09266 0.08931 -0.0692 0.0092 1.0000
15.750 1.4406 0.10006 0.09692 -0.0723 0.0092 1.0000
16.000 1.4196 0.10821 0.10527 -0.0761 0.0092 1.0000
16.250 1.3971 0.11715 0.11440 -0.0806 0.0092 1.0000
16.500 1.3730 0.12694 0.12439 -0.0860 0.0092 1.0000
16.750 1.3473 0.13769 0.13533 -0.0923 0.0093 1.0000
17.000 1.3187 0.15006 0.14788 -0.1000 0.0095 1.0000
17.250 1.2832 0.16597 0.16396 -0.1102 0.0097 1.0000
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