ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 100,000 Max Cl/Cd: 61.13 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor07-il-100000.txt Download as CSV file: xf-hor07-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4276 0.11625 0.11139 -0.0024 1.0000 0.0711
-8.500 -0.4318 0.11542 0.11064 -0.0074 1.0000 0.0719
-8.250 -0.4329 0.11398 0.10928 -0.0132 1.0000 0.0722
-8.000 -0.4100 0.10554 0.10081 -0.0071 1.0000 0.0741
-7.750 -0.3984 0.10187 0.09716 -0.0069 1.0000 0.0764
-7.500 -0.3909 0.09885 0.09416 -0.0080 1.0000 0.0790
-7.250 -0.3860 0.09614 0.09151 -0.0102 1.0000 0.0821
-7.000 -0.3745 0.09482 0.09023 -0.0259 1.0000 0.0852
-6.750 -0.3663 0.08944 0.08492 -0.0231 1.0000 0.0866
-6.500 -0.3551 0.08583 0.08134 -0.0188 1.0000 0.0900
-6.250 -0.3406 0.08272 0.07826 -0.0223 1.0000 0.0954
-6.000 -0.3147 0.07869 0.07421 -0.0371 1.0000 0.1001
-5.750 -0.3071 0.07508 0.07067 -0.0324 1.0000 0.1022
-5.500 -0.2920 0.07197 0.06760 -0.0331 1.0000 0.1062
-5.250 -0.2549 0.06760 0.06313 -0.0484 1.0000 0.1146
-5.000 -0.2502 0.06462 0.06026 -0.0445 1.0000 0.1164
-4.750 -0.2160 0.06254 0.05796 -0.0559 1.0000 0.1280
-4.500 -0.2229 0.06009 0.05565 -0.0525 1.0000 0.1289
-4.250 -0.2278 0.05823 0.05389 -0.0486 1.0000 0.1300
-4.000 -0.1916 0.05445 0.05009 -0.0524 0.9940 0.1364
-3.750 -0.1154 0.04968 0.04483 -0.0697 0.9869 0.1576
-3.500 -0.0388 0.03436 0.02859 -0.0857 0.9847 0.0876
-3.250 0.0207 0.02699 0.02021 -0.0940 0.9803 0.0762
-3.000 0.0731 0.02296 0.01532 -0.0993 0.9743 0.0766
-2.750 0.1250 0.02079 0.01262 -0.1040 0.9696 0.0872
-2.500 0.1694 0.01941 0.01109 -0.1072 0.9600 0.1031
-2.250 0.2138 0.01842 0.00998 -0.1104 0.9510 0.1310
-2.000 0.2562 0.01765 0.00920 -0.1130 0.9411 0.1741
-1.750 0.2920 0.01725 0.00889 -0.1144 0.9282 0.2234
-1.500 0.3248 0.01698 0.00856 -0.1151 0.9142 0.2609
-1.250 0.3540 0.01678 0.00836 -0.1149 0.8994 0.2934
-1.000 0.3811 0.01651 0.00810 -0.1142 0.8845 0.3231
-0.750 0.4071 0.01621 0.00782 -0.1133 0.8700 0.3503
-0.500 0.4324 0.01599 0.00770 -0.1122 0.8563 0.3820
-0.250 0.4582 0.01569 0.00752 -0.1114 0.8436 0.4289
0.000 0.4812 0.01476 0.00745 -0.1099 0.8318 0.6325
0.500 0.5302 0.01458 0.00718 -0.1070 0.8069 1.0000
0.750 0.5567 0.01483 0.00726 -0.1064 0.7936 1.0000
1.000 0.5831 0.01509 0.00738 -0.1057 0.7805 1.0000
1.250 0.6095 0.01535 0.00752 -0.1051 0.7677 1.0000
1.500 0.6360 0.01562 0.00769 -0.1044 0.7554 1.0000
1.750 0.6623 0.01589 0.00784 -0.1037 0.7434 1.0000
2.000 0.6886 0.01615 0.00802 -0.1029 0.7312 1.0000
2.250 0.7154 0.01644 0.00827 -0.1025 0.7177 1.0000
2.500 0.7422 0.01674 0.00854 -0.1020 0.7045 1.0000
2.750 0.7690 0.01704 0.00883 -0.1016 0.6917 1.0000
3.000 0.7958 0.01732 0.00912 -0.1012 0.6793 1.0000
3.250 0.8226 0.01759 0.00936 -0.1006 0.6677 1.0000
3.500 0.8495 0.01785 0.00961 -0.1001 0.6565 1.0000
3.750 0.8769 0.01821 0.01008 -0.1000 0.6446 1.0000
4.000 0.9040 0.01857 0.01050 -0.0998 0.6336 1.0000
4.250 0.9310 0.01884 0.01080 -0.0993 0.6235 1.0000
4.500 0.9576 0.01899 0.01096 -0.0986 0.6114 1.0000
4.750 0.9833 0.01895 0.01100 -0.0976 0.5938 1.0000
5.000 1.0081 0.01864 0.01067 -0.0961 0.5704 1.0000
5.250 1.0329 0.01837 0.01040 -0.0947 0.5457 1.0000
5.500 1.0578 0.01819 0.01020 -0.0934 0.5204 1.0000
5.750 1.0823 0.01808 0.01019 -0.0923 0.4885 1.0000
6.000 1.1058 0.01809 0.01019 -0.0909 0.4423 1.0000
6.250 1.1178 0.01987 0.01070 -0.0885 0.1979 1.0000
6.500 1.1290 0.02311 0.01309 -0.0870 0.1192 1.0000
6.750 1.1477 0.02465 0.01459 -0.0858 0.1038 1.0000
7.000 1.1655 0.02615 0.01611 -0.0844 0.0957 1.0000
7.250 1.1830 0.02778 0.01772 -0.0828 0.0912 1.0000
7.500 1.2034 0.02926 0.01923 -0.0814 0.0875 1.0000
7.750 1.2256 0.03091 0.02086 -0.0803 0.0845 1.0000
8.000 1.2502 0.03303 0.02286 -0.0796 0.0817 1.0000
8.250 1.2757 0.03526 0.02521 -0.0790 0.0787 1.0000
8.500 1.3008 0.03727 0.02748 -0.0781 0.0767 1.0000
8.750 1.3255 0.03975 0.03025 -0.0773 0.0752 1.0000
9.000 1.3473 0.04224 0.03301 -0.0763 0.0724 1.0000
9.250 1.3682 0.04526 0.03615 -0.0757 0.0690 1.0000
9.500 1.3832 0.05005 0.04131 -0.0746 0.0664 1.0000
9.750 1.3930 0.05273 0.04462 -0.0722 0.0646 1.0000
10.000 1.3995 0.05631 0.04875 -0.0698 0.0628 1.0000
10.250 1.4018 0.06003 0.05294 -0.0674 0.0610 1.0000
10.500 1.3992 0.06442 0.05778 -0.0649 0.0606 1.0000
10.750 1.3900 0.06945 0.06325 -0.0622 0.0617 1.0000
11.000 1.3771 0.07450 0.06865 -0.0597 0.0630 1.0000
11.250 1.3617 0.07947 0.07387 -0.0574 0.0643 1.0000
11.500 1.2269 0.07453 0.06921 -0.0416 0.0637 1.0000
11.750 1.1994 0.07971 0.07459 -0.0406 0.0643 1.0000
12.000 1.1724 0.08536 0.08040 -0.0404 0.0650 1.0000
12.250 1.1465 0.09145 0.08662 -0.0408 0.0657 1.0000
12.500 1.0523 0.10368 0.09931 -0.0477 0.0756 1.0000
12.750 1.0159 0.11159 0.10730 -0.0513 0.0776 1.0000
13.000 1.0017 0.11712 0.11284 -0.0519 0.0794 1.0000
13.250 1.0684 0.17583 0.17126 -0.1119 0.1523 1.0000
13.500 1.0908 0.17827 0.17378 -0.1082 0.1433 1.0000
13.750 0.8157 0.16641 0.16200 -0.0860 0.1624 1.0000
14.000 0.8530 0.17085 0.16655 -0.0826 0.1543 1.0000
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Polar data table (+)
Polar graphs
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