ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR12 AIRFOIL (hor12-il) Reynolds number: 100,000 Max Cl/Cd: 54.73 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor12-il-100000.txt Download as CSV file: xf-hor12-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3987 0.12081 0.11554 -0.0088 1.0005 0.1261
-9.750 -0.4016 0.11832 0.11309 -0.0119 1.0005 0.1317
-9.500 -0.4337 0.11722 0.11212 -0.0206 1.0005 0.1335
-9.250 -0.3934 0.11074 0.10558 -0.0150 1.0005 0.1361
-9.000 -0.3787 0.10750 0.10234 -0.0146 1.0005 0.1392
-8.750 -0.3729 0.10449 0.09935 -0.0159 1.0005 0.1436
-8.500 -0.4072 0.10291 0.09793 -0.0248 1.0005 0.1485
-8.250 -0.3854 0.09764 0.09266 -0.0228 1.0005 0.1501
-8.000 -0.3594 0.09463 0.08962 -0.0202 1.0005 0.1545
-7.750 -0.3580 0.09196 0.08700 -0.0219 1.0005 0.1607
-7.500 -0.3864 0.08832 0.08355 -0.0319 1.0005 0.1646
-7.250 -0.4193 0.05741 0.05242 -0.0633 1.0005 0.1056
-7.000 -0.4119 0.04909 0.04385 -0.0704 1.0005 0.1026
-6.750 -0.3944 0.03921 0.03326 -0.0806 1.0005 0.1024
-6.500 -0.3681 0.03324 0.02632 -0.0866 1.0005 0.1047
-6.250 -0.3508 0.03087 0.02390 -0.0867 1.0005 0.1069
-6.000 -0.3338 0.02955 0.02249 -0.0863 1.0005 0.1094
-5.750 -0.3151 0.02820 0.02094 -0.0864 1.0005 0.1130
-5.500 -0.2913 0.02654 0.01871 -0.0876 1.0005 0.1191
-5.250 -0.2691 0.02575 0.01808 -0.0879 0.9995 0.1248
-5.000 -0.2183 0.02409 0.01616 -0.0931 0.9935 0.1383
-4.750 -0.1697 0.02309 0.01507 -0.0976 0.9853 0.1559
-4.500 -0.1208 0.02241 0.01428 -0.1021 0.9773 0.1742
-4.250 -0.0704 0.02201 0.01371 -0.1068 0.9696 0.1947
-4.000 -0.0233 0.02149 0.01316 -0.1108 0.9605 0.2117
-3.750 0.0278 0.02080 0.01246 -0.1153 0.9544 0.2287
-3.500 0.0707 0.02029 0.01197 -0.1183 0.9436 0.2459
-3.250 0.1121 0.01978 0.01149 -0.1208 0.9327 0.2638
-3.000 0.1512 0.01931 0.01105 -0.1227 0.9212 0.2821
-2.750 0.1873 0.01890 0.01066 -0.1239 0.9093 0.3009
-2.500 0.2182 0.01863 0.01038 -0.1240 0.8950 0.3201
-2.250 0.2476 0.01842 0.01017 -0.1238 0.8807 0.3417
-2.000 0.2753 0.01828 0.01011 -0.1232 0.8667 0.3620
-1.750 0.3027 0.01820 0.01005 -0.1225 0.8529 0.3850
-1.500 0.3297 0.01813 0.00999 -0.1216 0.8397 0.4088
-1.250 0.3561 0.01807 0.00994 -0.1206 0.8272 0.4333
-1.000 0.3826 0.01802 0.00991 -0.1197 0.8138 0.4591
-0.750 0.4094 0.01800 0.00989 -0.1190 0.8000 0.4879
-0.500 0.4360 0.01792 0.00987 -0.1183 0.7870 0.5166
-0.250 0.4625 0.01781 0.00981 -0.1174 0.7749 0.5474
0.000 0.4887 0.01767 0.00971 -0.1164 0.7636 0.5800
0.250 0.5152 0.01760 0.00974 -0.1158 0.7503 0.6153
0.500 0.5411 0.01752 0.00978 -0.1149 0.7378 0.6524
0.750 0.5663 0.01743 0.00981 -0.1137 0.7264 0.6966
1.000 0.5892 0.01723 0.00979 -0.1119 0.7155 0.7553
1.250 0.6039 0.01670 0.00965 -0.1081 0.7033 0.9292
1.500 0.6380 0.01694 0.00967 -0.1096 0.6912 0.9995
1.750 0.6686 0.01717 0.00966 -0.1098 0.6809 0.9995
2.000 0.6981 0.01746 0.00986 -0.1101 0.6683 0.9995
2.250 0.7271 0.01778 0.01009 -0.1102 0.6563 0.9995
2.500 0.7559 0.01805 0.01023 -0.1101 0.6457 0.9995
2.750 0.7845 0.01831 0.01040 -0.1100 0.6347 0.9995
3.000 0.8128 0.01865 0.01071 -0.1100 0.6226 0.9995
3.250 0.8411 0.01896 0.01095 -0.1098 0.6120 0.9995
3.500 0.8695 0.01921 0.01111 -0.1095 0.6018 0.9995
3.750 0.8973 0.01959 0.01150 -0.1095 0.5897 0.9995
4.000 0.9251 0.01992 0.01181 -0.1093 0.5788 0.9995
4.250 0.9535 0.02016 0.01195 -0.1089 0.5690 0.9995
4.500 0.9807 0.02055 0.01239 -0.1087 0.5567 0.9995
4.750 1.0081 0.02092 0.01277 -0.1085 0.5455 0.9995
5.000 1.0365 0.02116 0.01291 -0.1081 0.5363 0.9995
5.250 1.0631 0.02159 0.01343 -0.1079 0.5239 0.9995
5.500 1.0900 0.02201 0.01389 -0.1076 0.5125 0.9995
5.750 1.1177 0.02231 0.01413 -0.1072 0.5022 0.9995
6.000 1.1445 0.02265 0.01451 -0.1068 0.4904 0.9995
6.250 1.1705 0.02310 0.01503 -0.1064 0.4780 0.9995
6.500 1.1969 0.02349 0.01545 -0.1059 0.4662 0.9995
6.750 1.2240 0.02378 0.01569 -0.1054 0.4549 0.9995
7.000 1.2499 0.02407 0.01601 -0.1049 0.4417 0.9995
7.250 1.2748 0.02435 0.01635 -0.1041 0.4271 0.9995
7.500 1.2995 0.02448 0.01647 -0.1033 0.4110 0.9995
7.750 1.3237 0.02454 0.01650 -0.1024 0.3938 0.9995
8.000 1.3469 0.02472 0.01666 -0.1014 0.3764 0.9995
8.250 1.3692 0.02503 0.01705 -0.1004 0.3595 0.9995
8.500 1.3912 0.02542 0.01754 -0.0994 0.3431 0.9995
8.750 1.4121 0.02586 0.01806 -0.0983 0.3257 0.9995
9.000 1.4320 0.02637 0.01865 -0.0970 0.3074 0.9995
9.250 1.4501 0.02693 0.01926 -0.0956 0.2875 0.9995
9.500 1.4658 0.02763 0.01998 -0.0939 0.2651 0.9995
9.750 1.4777 0.02856 0.02089 -0.0917 0.2389 0.9995
10.000 1.4845 0.02990 0.02215 -0.0891 0.2092 0.9995
10.250 1.4858 0.03173 0.02382 -0.0860 0.1805 0.9995
10.500 1.4835 0.03386 0.02580 -0.0825 0.1581 0.9995
10.750 1.4795 0.03598 0.02782 -0.0788 0.1429 0.9995
11.000 1.4781 0.03820 0.02993 -0.0758 0.1318 0.9995
11.250 1.4799 0.04036 0.03204 -0.0734 0.1227 0.9995
11.500 1.4848 0.04253 0.03426 -0.0714 0.1150 0.9995
11.750 1.4924 0.04456 0.03618 -0.0696 0.1089 0.9995
12.000 1.5019 0.04668 0.03842 -0.0680 0.1038 0.9995
12.250 1.5099 0.04874 0.04055 -0.0665 0.0991 0.9995
12.500 1.5290 0.05066 0.04228 -0.0654 0.0940 0.9995
12.750 1.5311 0.05311 0.04505 -0.0638 0.0911 0.9995
13.000 1.5358 0.05552 0.04763 -0.0625 0.0878 0.9995
13.250 1.5471 0.05759 0.04968 -0.0614 0.0844 0.9995
13.500 1.5631 0.06024 0.05235 -0.0603 0.0811 0.9995
13.750 1.5571 0.06343 0.05587 -0.0590 0.0794 0.9995
14.000 1.5521 0.06680 0.05950 -0.0581 0.0775 0.9995
14.250 1.5473 0.07028 0.06321 -0.0574 0.0756 0.9995
14.500 1.5444 0.07375 0.06686 -0.0568 0.0739 0.9995
14.750 1.5537 0.07649 0.06960 -0.0560 0.0716 0.9995
15.000 1.5499 0.08111 0.07436 -0.0556 0.0700 0.9995
15.250 1.5277 0.08640 0.07998 -0.0563 0.0696 0.9995
15.500 1.5037 0.09233 0.08622 -0.0577 0.0693 0.9995
15.750 1.4776 0.09896 0.09315 -0.0600 0.0691 0.9995
16.000 1.4494 0.10635 0.10083 -0.0631 0.0691 0.9995
16.250 1.4189 0.11475 0.10950 -0.0675 0.0693 0.9995
16.500 1.3864 0.12434 0.11932 -0.0731 0.0696 0.9995
16.750 1.3521 0.13531 0.13050 -0.0800 0.0701 0.9995
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