ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR12 AIRFOIL (hor12-il) Reynolds number: 200,000 Max Cl/Cd: 76.52 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor12-il-200000.txt Download as CSV file: xf-hor12-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3306 0.09781 0.09438 -0.0294 1.0005 0.0907
-9.250 -0.4038 0.10337 0.09971 -0.0158 1.0005 0.0854
-9.000 -0.5860 0.03950 0.03505 -0.0814 1.0005 0.0556
-8.750 -0.5665 0.03304 0.02781 -0.0884 1.0005 0.0566
-8.500 -0.5415 0.02920 0.02343 -0.0918 1.0005 0.0581
-8.250 -0.5163 0.02730 0.02149 -0.0928 1.0005 0.0598
-8.000 -0.4899 0.02581 0.01985 -0.0936 1.0005 0.0613
-7.750 -0.4634 0.02428 0.01812 -0.0944 1.0005 0.0629
-7.500 -0.4376 0.02296 0.01659 -0.0949 1.0005 0.0648
-7.250 -0.4132 0.02193 0.01532 -0.0949 1.0005 0.0667
-7.000 -0.3911 0.02058 0.01380 -0.0947 1.0005 0.0685
-6.750 -0.3725 0.01973 0.01298 -0.0938 1.0005 0.0703
-6.500 -0.3465 0.01911 0.01234 -0.0942 0.9986 0.0726
-6.250 -0.3020 0.01826 0.01135 -0.0978 0.9937 0.0767
-6.000 -0.2589 0.01710 0.01010 -0.1012 0.9876 0.0809
-5.750 -0.2139 0.01631 0.00931 -0.1048 0.9825 0.0874
-5.500 -0.1716 0.01549 0.00850 -0.1079 0.9737 0.0981
-5.250 -0.1296 0.01492 0.00792 -0.1109 0.9645 0.1147
-5.000 -0.0899 0.01452 0.00749 -0.1132 0.9538 0.1294
-4.750 -0.0560 0.01423 0.00716 -0.1142 0.9395 0.1407
-4.500 -0.0273 0.01404 0.00689 -0.1140 0.9210 0.1508
-4.250 -0.0001 0.01389 0.00671 -0.1135 0.9034 0.1604
-4.000 0.0265 0.01368 0.00647 -0.1128 0.8869 0.1698
-3.750 0.0534 0.01358 0.00626 -0.1122 0.8711 0.1808
-3.500 0.0805 0.01344 0.00610 -0.1117 0.8561 0.1918
-3.250 0.1079 0.01329 0.00591 -0.1112 0.8417 0.2033
-3.000 0.1356 0.01318 0.00575 -0.1108 0.8281 0.2169
-2.750 0.1639 0.01307 0.00561 -0.1106 0.8140 0.2320
-2.500 0.1925 0.01295 0.00546 -0.1105 0.8003 0.2480
-2.250 0.2211 0.01283 0.00534 -0.1105 0.7872 0.2657
-2.000 0.2497 0.01275 0.00525 -0.1103 0.7747 0.2855
-1.750 0.2782 0.01271 0.00518 -0.1102 0.7630 0.3070
-1.500 0.3073 0.01265 0.00517 -0.1102 0.7501 0.3294
-1.250 0.3364 0.01263 0.00517 -0.1103 0.7380 0.3533
-1.000 0.3653 0.01262 0.00518 -0.1102 0.7269 0.3772
-0.750 0.3943 0.01265 0.00520 -0.1101 0.7156 0.4035
-0.500 0.4234 0.01266 0.00527 -0.1102 0.7036 0.4293
-0.250 0.4524 0.01272 0.00531 -0.1101 0.6925 0.4565
0.000 0.4811 0.01276 0.00534 -0.1100 0.6821 0.4820
0.250 0.5101 0.01275 0.00538 -0.1100 0.6701 0.5073
0.500 0.5390 0.01276 0.00540 -0.1100 0.6592 0.5318
0.750 0.5675 0.01275 0.00540 -0.1098 0.6492 0.5561
1.000 0.5962 0.01271 0.00544 -0.1098 0.6373 0.5826
1.250 0.6246 0.01266 0.00550 -0.1097 0.6266 0.6119
1.500 0.6526 0.01262 0.00553 -0.1094 0.6168 0.6500
1.750 0.6793 0.01243 0.00564 -0.1089 0.6053 0.7161
2.000 0.6972 0.01186 0.00546 -0.1059 0.5957 0.9995
2.250 0.7272 0.01204 0.00549 -0.1062 0.5855 0.9995
2.500 0.7569 0.01221 0.00560 -0.1065 0.5741 0.9995
2.750 0.7862 0.01241 0.00570 -0.1066 0.5639 0.9995
3.000 0.8153 0.01260 0.00580 -0.1067 0.5537 0.9995
3.250 0.8443 0.01279 0.00596 -0.1068 0.5425 0.9995
3.500 0.8731 0.01300 0.00610 -0.1069 0.5322 0.9995
3.750 0.9018 0.01321 0.00624 -0.1069 0.5217 0.9995
4.000 0.9304 0.01342 0.00644 -0.1069 0.5106 0.9995
4.250 0.9589 0.01367 0.00664 -0.1069 0.5008 0.9995
4.500 0.9872 0.01391 0.00684 -0.1069 0.4906 0.9995
4.750 1.0154 0.01416 0.00709 -0.1069 0.4798 0.9995
5.000 1.0434 0.01444 0.00732 -0.1068 0.4696 0.9995
5.250 1.0711 0.01467 0.00753 -0.1067 0.4580 0.9995
5.500 1.0987 0.01490 0.00778 -0.1065 0.4458 0.9995
5.750 1.1261 0.01515 0.00804 -0.1064 0.4341 0.9995
6.000 1.1532 0.01543 0.00826 -0.1062 0.4224 0.9995
6.250 1.1801 0.01568 0.00850 -0.1059 0.4096 0.9995
6.500 1.2066 0.01592 0.00877 -0.1056 0.3954 0.9995
6.750 1.2328 0.01618 0.00904 -0.1053 0.3805 0.9995
7.000 1.2588 0.01647 0.00934 -0.1050 0.3659 0.9995
7.250 1.2848 0.01679 0.00969 -0.1047 0.3526 0.9995
7.500 1.3104 0.01715 0.01008 -0.1043 0.3396 0.9995
7.750 1.3354 0.01752 0.01046 -0.1038 0.3252 0.9995
8.000 1.3600 0.01793 0.01087 -0.1034 0.3099 0.9995
8.250 1.3841 0.01836 0.01133 -0.1028 0.2935 0.9995
8.500 1.4076 0.01884 0.01183 -0.1022 0.2759 0.9995
8.750 1.4301 0.01939 0.01237 -0.1015 0.2571 0.9995
9.000 1.4512 0.02005 0.01299 -0.1006 0.2364 0.9995
9.250 1.4712 0.02081 0.01372 -0.0996 0.2114 0.9995
9.500 1.4879 0.02184 0.01463 -0.0982 0.1814 0.9995
9.750 1.4996 0.02328 0.01587 -0.0963 0.1456 0.9995
10.000 1.5062 0.02508 0.01744 -0.0938 0.1147 0.9995
10.250 1.5105 0.02687 0.01911 -0.0909 0.0977 0.9995
10.500 1.5142 0.02850 0.02074 -0.0879 0.0886 0.9995
10.750 1.5111 0.03033 0.02255 -0.0842 0.0831 0.9995
11.000 1.5139 0.03204 0.02435 -0.0816 0.0787 0.9995
11.250 1.5173 0.03386 0.02624 -0.0795 0.0748 0.9995
11.500 1.5161 0.03621 0.02860 -0.0775 0.0718 0.9995
11.750 1.5169 0.03857 0.03103 -0.0758 0.0693 0.9995
12.000 1.5219 0.04064 0.03322 -0.0746 0.0669 0.9995
12.250 1.5256 0.04292 0.03558 -0.0735 0.0646 0.9995
12.500 1.5278 0.04538 0.03812 -0.0726 0.0626 0.9995
12.750 1.5280 0.04808 0.04081 -0.0714 0.0607 0.9995
13.000 1.5308 0.05053 0.04331 -0.0701 0.0590 0.9995
13.250 1.5350 0.05294 0.04588 -0.0694 0.0576 0.9995
13.500 1.5383 0.05545 0.04851 -0.0687 0.0559 0.9995
13.750 1.5410 0.05805 0.05120 -0.0681 0.0543 0.9995
14.000 1.5431 0.06069 0.05389 -0.0676 0.0527 0.9995
14.250 1.5465 0.06314 0.05634 -0.0665 0.0510 0.9995
14.500 1.5505 0.06565 0.05893 -0.0653 0.0495 0.9995
14.750 1.5501 0.06875 0.06222 -0.0651 0.0484 0.9995
15.000 1.5491 0.07196 0.06560 -0.0650 0.0471 0.9995
15.250 1.5477 0.07525 0.06902 -0.0651 0.0458 0.9995
15.500 1.5470 0.07847 0.07233 -0.0652 0.0445 0.9995
15.750 1.5488 0.08130 0.07517 -0.0651 0.0432 0.9995
16.000 1.5505 0.08423 0.07813 -0.0641 0.0415 0.9995
16.250 1.5411 0.08893 0.08307 -0.0656 0.0407 0.9995
16.500 1.5327 0.09367 0.08803 -0.0672 0.0398 0.9995
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