ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 100,000 Max Cl/Cd: 59.53 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor07-il-100000-n5.txt Download as CSV file: xf-hor07-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4260 0.11376 0.10886 -0.0030 1.0000 0.0487
-8.500 -0.4256 0.11158 0.10674 -0.0071 1.0000 0.0494
-8.250 -0.4237 0.10902 0.10424 -0.0108 1.0000 0.0497
-8.000 -0.4180 0.10597 0.10124 -0.0149 1.0000 0.0499
-7.750 -0.4069 0.10012 0.09542 -0.0110 1.0000 0.0514
-7.500 -0.3948 0.09670 0.09202 -0.0103 1.0000 0.0531
-7.250 -0.3868 0.09358 0.08894 -0.0117 1.0000 0.0542
-7.000 -0.3771 0.09024 0.08563 -0.0143 1.0000 0.0551
-6.750 -0.3660 0.08676 0.08219 -0.0174 1.0000 0.0559
-6.250 -0.3278 0.07428 0.06965 -0.0363 1.0000 0.0380
-6.000 -0.3167 0.07124 0.06665 -0.0356 1.0000 0.0364
-5.750 -0.2982 0.06708 0.06250 -0.0396 1.0000 0.0347
-5.500 -0.2750 0.06207 0.05744 -0.0456 1.0000 0.0330
-5.000 -0.1927 0.04273 0.03756 -0.0704 1.0000 0.0287
-4.750 -0.1418 0.03411 0.02826 -0.0815 0.9885 0.0285
-4.500 -0.0942 0.02824 0.02160 -0.0892 0.9743 0.0296
-4.250 -0.0549 0.02624 0.01935 -0.0929 0.9566 0.0321
-4.000 -0.0137 0.02340 0.01588 -0.0965 0.9389 0.0339
-3.750 0.0238 0.02117 0.01308 -0.0987 0.9192 0.0354
-3.500 0.0573 0.01964 0.01107 -0.0996 0.8982 0.0374
-3.250 0.0880 0.01838 0.00955 -0.0999 0.8794 0.0402
-3.000 0.1167 0.01768 0.00869 -0.0999 0.8624 0.0465
-2.750 0.1451 0.01699 0.00786 -0.0998 0.8471 0.0567
-2.500 0.1735 0.01640 0.00716 -0.0996 0.8326 0.0710
-2.250 0.2017 0.01598 0.00673 -0.0995 0.8188 0.0930
-2.000 0.2297 0.01568 0.00643 -0.0993 0.8058 0.1255
-1.750 0.2576 0.01557 0.00625 -0.0991 0.7933 0.1596
-1.500 0.2852 0.01547 0.00609 -0.0988 0.7811 0.1826
-1.250 0.3126 0.01543 0.00597 -0.0984 0.7688 0.2083
-0.750 0.3671 0.01525 0.00568 -0.0977 0.7431 0.2550
-0.500 0.3947 0.01513 0.00552 -0.0974 0.7304 0.2753
-0.250 0.4224 0.01504 0.00538 -0.0971 0.7188 0.2991
0.000 0.4501 0.01494 0.00524 -0.0969 0.7087 0.3284
0.500 0.5058 0.01441 0.00522 -0.0968 0.6881 0.4829
0.750 0.5269 0.01338 0.00497 -0.0947 0.6788 1.0000
1.000 0.5554 0.01352 0.00499 -0.0947 0.6678 1.0000
1.250 0.5836 0.01367 0.00501 -0.0946 0.6573 1.0000
1.500 0.6116 0.01383 0.00504 -0.0944 0.6473 1.0000
1.750 0.6398 0.01398 0.00514 -0.0944 0.6359 1.0000
2.000 0.6678 0.01414 0.00524 -0.0943 0.6250 1.0000
2.250 0.6956 0.01431 0.00534 -0.0941 0.6149 1.0000
2.500 0.7235 0.01449 0.00548 -0.0940 0.6042 1.0000
2.750 0.7515 0.01468 0.00567 -0.0939 0.5931 1.0000
3.000 0.7792 0.01488 0.00585 -0.0937 0.5826 1.0000
3.250 0.8068 0.01509 0.00604 -0.0936 0.5723 1.0000
3.500 0.8346 0.01532 0.00630 -0.0935 0.5610 1.0000
3.750 0.8622 0.01555 0.00660 -0.0934 0.5504 1.0000
4.000 0.8896 0.01579 0.00685 -0.0932 0.5402 1.0000
4.250 0.9171 0.01604 0.00718 -0.0930 0.5286 1.0000
4.500 0.9442 0.01628 0.00745 -0.0928 0.5137 1.0000
4.750 0.9703 0.01648 0.00767 -0.0923 0.4893 1.0000
5.000 0.9955 0.01674 0.00781 -0.0917 0.4547 1.0000
5.250 1.0203 0.01714 0.00807 -0.0911 0.4173 1.0000
5.500 1.0453 0.01760 0.00847 -0.0906 0.3775 1.0000
5.750 1.0684 0.01834 0.00897 -0.0900 0.3141 1.0000
6.000 1.0842 0.02054 0.01014 -0.0893 0.1434 1.0000
6.250 1.1028 0.02238 0.01157 -0.0885 0.0847 1.0000
6.500 1.1238 0.02364 0.01284 -0.0878 0.0710 1.0000
6.750 1.1446 0.02482 0.01411 -0.0870 0.0644 1.0000
7.000 1.1650 0.02592 0.01540 -0.0861 0.0600 1.0000
7.250 1.1834 0.02719 0.01676 -0.0850 0.0564 1.0000
7.500 1.2002 0.02857 0.01821 -0.0837 0.0536 1.0000
7.750 1.2185 0.02970 0.01950 -0.0825 0.0510 1.0000
8.000 1.2354 0.03100 0.02091 -0.0811 0.0491 1.0000
8.250 1.2521 0.03238 0.02241 -0.0796 0.0476 1.0000
8.500 1.2690 0.03384 0.02394 -0.0782 0.0463 1.0000
8.750 1.2864 0.03542 0.02557 -0.0769 0.0450 1.0000
9.000 1.3050 0.03722 0.02741 -0.0758 0.0439 1.0000
9.250 1.3265 0.03966 0.02988 -0.0750 0.0427 1.0000
9.500 1.3457 0.04133 0.03184 -0.0738 0.0415 1.0000
9.750 1.3630 0.04310 0.03392 -0.0725 0.0396 1.0000
10.000 1.3784 0.04501 0.03610 -0.0712 0.0374 1.0000
10.250 1.3890 0.04654 0.03780 -0.0697 0.0348 1.0000
10.500 1.4001 0.04879 0.04003 -0.0686 0.0324 1.0000
10.750 1.4059 0.05109 0.04275 -0.0664 0.0307 1.0000
11.000 1.4095 0.05391 0.04597 -0.0641 0.0293 1.0000
11.250 1.4080 0.05674 0.04913 -0.0614 0.0280 1.0000
11.500 1.4035 0.05944 0.05210 -0.0589 0.0269 1.0000
11.750 1.3978 0.06217 0.05507 -0.0570 0.0260 1.0000
12.000 1.3922 0.06497 0.05803 -0.0558 0.0251 1.0000
12.250 1.3866 0.06810 0.06128 -0.0550 0.0243 1.0000
12.500 1.3768 0.07245 0.06576 -0.0545 0.0237 1.0000
12.750 1.3593 0.07733 0.07100 -0.0549 0.0234 1.0000
13.000 1.3403 0.08286 0.07686 -0.0560 0.0231 1.0000
13.250 1.3205 0.08896 0.08325 -0.0579 0.0229 1.0000
13.500 1.2997 0.09561 0.09016 -0.0605 0.0229 1.0000
13.750 1.2784 0.10281 0.09760 -0.0639 0.0229 1.0000
14.000 1.2569 0.11055 0.10554 -0.0681 0.0229 1.0000
14.250 1.2353 0.11893 0.11410 -0.0731 0.0231 1.0000
14.500 1.2144 0.12803 0.12331 -0.0789 0.0233 1.0000
14.750 1.1949 0.13768 0.13308 -0.0851 0.0235 1.0000
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