ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: ONERA HOR12 AIRFOIL (hor12-il) Reynolds number: 100,000 Max Cl/Cd: 57.79 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor12-il-100000-n5.txt Download as CSV file: xf-hor12-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR12 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4733 0.10211 0.09672 -0.0206 1.0005 0.0493
-10.000 -0.4669 0.09909 0.09372 -0.0218 1.0005 0.0499
-9.500 -0.6214 0.04843 0.04271 -0.0699 1.0005 0.0489
-9.250 -0.6089 0.04381 0.03786 -0.0754 1.0005 0.0496
-9.000 -0.5902 0.04098 0.03488 -0.0785 1.0005 0.0507
-8.750 -0.5695 0.03814 0.03181 -0.0816 1.0005 0.0523
-8.500 -0.5470 0.03486 0.02814 -0.0851 1.0005 0.0543
-8.250 -0.5224 0.03173 0.02454 -0.0879 1.0005 0.0561
-8.000 -0.4966 0.02929 0.02169 -0.0898 1.0005 0.0576
-7.750 -0.4720 0.02817 0.02060 -0.0903 1.0005 0.0594
-7.500 -0.4471 0.02713 0.01949 -0.0908 1.0005 0.0617
-7.250 -0.4223 0.02587 0.01806 -0.0913 1.0005 0.0641
-7.000 -0.3980 0.02456 0.01653 -0.0916 1.0005 0.0664
-6.750 -0.3749 0.02353 0.01541 -0.0916 1.0005 0.0686
-6.500 -0.3443 0.02275 0.01463 -0.0929 0.9962 0.0722
-6.250 -0.3035 0.02172 0.01337 -0.0961 0.9871 0.0783
-6.000 -0.2636 0.02087 0.01252 -0.0991 0.9773 0.0847
-5.750 -0.2236 0.02001 0.01155 -0.1019 0.9674 0.0934
-5.500 -0.1850 0.01938 0.01080 -0.1044 0.9561 0.1038
-5.250 -0.1474 0.01887 0.01026 -0.1065 0.9441 0.1138
-5.000 -0.1118 0.01846 0.00978 -0.1082 0.9303 0.1244
-4.750 -0.0784 0.01815 0.00939 -0.1093 0.9149 0.1367
-4.500 -0.0463 0.01789 0.00902 -0.1100 0.8991 0.1491
-4.250 -0.0158 0.01763 0.00873 -0.1104 0.8833 0.1600
-4.000 0.0138 0.01737 0.00841 -0.1106 0.8677 0.1700
-3.750 0.0429 0.01715 0.00813 -0.1105 0.8524 0.1820
-3.500 0.0716 0.01698 0.00786 -0.1104 0.8376 0.1950
-3.250 0.1001 0.01681 0.00766 -0.1103 0.8233 0.2082
-3.000 0.1285 0.01664 0.00744 -0.1101 0.8098 0.2216
-2.750 0.1569 0.01646 0.00721 -0.1099 0.7966 0.2348
-2.500 0.1856 0.01630 0.00701 -0.1099 0.7833 0.2493
-2.250 0.2142 0.01616 0.00685 -0.1098 0.7706 0.2653
-2.000 0.2426 0.01604 0.00672 -0.1096 0.7586 0.2820
-1.750 0.2710 0.01596 0.00662 -0.1094 0.7472 0.3005
-1.500 0.2998 0.01590 0.00657 -0.1094 0.7346 0.3212
-1.250 0.3285 0.01587 0.00654 -0.1094 0.7228 0.3433
-1.000 0.3570 0.01586 0.00654 -0.1092 0.7117 0.3662
-0.750 0.3857 0.01587 0.00655 -0.1091 0.7001 0.3914
-0.500 0.4144 0.01588 0.00659 -0.1090 0.6884 0.4160
-0.250 0.4429 0.01592 0.00660 -0.1089 0.6776 0.4410
0.000 0.4713 0.01594 0.00662 -0.1087 0.6669 0.4649
0.250 0.5000 0.01597 0.00666 -0.1086 0.6555 0.4891
0.500 0.5283 0.01599 0.00668 -0.1085 0.6452 0.5127
0.750 0.5566 0.01600 0.00670 -0.1083 0.6346 0.5373
1.000 0.5848 0.01600 0.00676 -0.1081 0.6235 0.5632
1.250 0.6126 0.01599 0.00682 -0.1078 0.6136 0.5923
1.500 0.6400 0.01595 0.00689 -0.1074 0.6029 0.6287
2.000 0.6871 0.01558 0.00700 -0.1046 0.5832 0.7996
2.250 0.7122 0.01543 0.00694 -0.1036 0.5723 0.9995
2.500 0.7415 0.01566 0.00707 -0.1038 0.5619 0.9995
2.750 0.7704 0.01588 0.00718 -0.1039 0.5524 0.9995
3.000 0.7993 0.01612 0.00738 -0.1040 0.5412 0.9995
3.250 0.8279 0.01637 0.00757 -0.1041 0.5311 0.9995
3.500 0.8563 0.01662 0.00775 -0.1040 0.5213 0.9995
3.750 0.8847 0.01689 0.00801 -0.1041 0.5106 0.9995
4.000 0.9128 0.01716 0.00823 -0.1040 0.5009 0.9995
4.250 0.9407 0.01744 0.00850 -0.1039 0.4907 0.9995
4.500 0.9685 0.01775 0.00880 -0.1038 0.4800 0.9995
4.750 0.9961 0.01805 0.00906 -0.1037 0.4702 0.9995
5.000 1.0236 0.01837 0.00942 -0.1036 0.4594 0.9995
5.250 1.0509 0.01871 0.00978 -0.1034 0.4491 0.9995
5.500 1.0779 0.01905 0.01009 -0.1032 0.4397 0.9995
5.750 1.1048 0.01941 0.01051 -0.1030 0.4285 0.9995
6.000 1.1314 0.01977 0.01092 -0.1027 0.4178 0.9995
6.250 1.1576 0.02015 0.01128 -0.1024 0.4074 0.9995
6.500 1.1836 0.02054 0.01174 -0.1020 0.3957 0.9995
6.750 1.2093 0.02095 0.01223 -0.1017 0.3839 0.9995
7.000 1.2344 0.02136 0.01267 -0.1012 0.3715 0.9995
7.250 1.2589 0.02179 0.01312 -0.1007 0.3577 0.9995
7.500 1.2825 0.02222 0.01359 -0.1000 0.3404 0.9995
7.750 1.3050 0.02270 0.01409 -0.0992 0.3204 0.9995
8.000 1.3265 0.02326 0.01460 -0.0984 0.2997 0.9995
8.250 1.3479 0.02387 0.01524 -0.0975 0.2797 0.9995
8.500 1.3688 0.02454 0.01595 -0.0966 0.2618 0.9995
8.750 1.3887 0.02529 0.01672 -0.0956 0.2436 0.9995
9.000 1.4070 0.02614 0.01756 -0.0945 0.2250 0.9995
9.250 1.4239 0.02708 0.01850 -0.0932 0.2060 0.9995
9.500 1.4390 0.02815 0.01956 -0.0917 0.1855 0.9995
9.750 1.4507 0.02942 0.02080 -0.0899 0.1652 0.9995
10.000 1.4601 0.03083 0.02218 -0.0878 0.1454 0.9995
10.250 1.4660 0.03240 0.02372 -0.0855 0.1280 0.9995
10.500 1.4672 0.03410 0.02541 -0.0826 0.1146 0.9995
10.750 1.4660 0.03605 0.02737 -0.0798 0.1045 0.9995
11.000 1.4643 0.03829 0.02963 -0.0775 0.0962 0.9995
11.250 1.4632 0.04068 0.03212 -0.0758 0.0898 0.9995
11.500 1.4601 0.04344 0.03494 -0.0744 0.0845 0.9995
11.750 1.4564 0.04646 0.03802 -0.0734 0.0804 0.9995
12.000 1.4548 0.04942 0.04112 -0.0727 0.0764 0.9995
12.250 1.4508 0.05275 0.04453 -0.0722 0.0732 0.9995
12.500 1.4444 0.05645 0.04827 -0.0720 0.0707 0.9995
12.750 1.4424 0.05971 0.05166 -0.0717 0.0682 0.9995
13.000 1.4403 0.06306 0.05514 -0.0715 0.0658 0.9995
13.250 1.4372 0.06654 0.05873 -0.0715 0.0638 0.9995
13.500 1.4334 0.07017 0.06246 -0.0716 0.0619 0.9995
13.750 1.4288 0.07385 0.06617 -0.0717 0.0602 0.9995
14.000 1.4271 0.07722 0.06964 -0.0717 0.0585 0.9995
14.250 1.4257 0.08069 0.07327 -0.0719 0.0567 0.9995
14.500 1.4243 0.08423 0.07694 -0.0722 0.0550 0.9995
14.750 1.4225 0.08787 0.08068 -0.0726 0.0534 0.9995
15.000 1.4204 0.09155 0.08444 -0.0732 0.0520 0.9995
15.250 1.4196 0.09498 0.08789 -0.0736 0.0506 0.9995
15.500 1.4191 0.09849 0.09151 -0.0740 0.0493 0.9995
15.750 1.4166 0.10258 0.09582 -0.0750 0.0481 0.9995
16.000 1.4132 0.10684 0.10026 -0.0763 0.0468 0.9995
16.250 1.4099 0.11116 0.10472 -0.0777 0.0456 0.9995
16.500 1.4073 0.11536 0.10903 -0.0791 0.0444 0.9995
16.750 1.4058 0.11935 0.11311 -0.0805 0.0434 0.9995
17.000 1.4073 0.12265 0.11643 -0.0814 0.0423 0.9995
17.250 1.4057 0.12667 0.12054 -0.0828 0.0414 0.9995
17.500 1.3946 0.13313 0.12726 -0.0863 0.0407 0.9995
17.750 1.3822 0.14007 0.13446 -0.0904 0.0400 0.9995
18.000 1.3681 0.14765 0.14228 -0.0951 0.0393 0.9995
18.250 1.3512 0.15626 0.15113 -0.1008 0.0388 0.9995
18.500 1.3278 0.16709 0.16220 -0.1083 0.0384 0.9995
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