ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA HOR12 AIRFOIL (hor12-il) Reynolds number: 50,000 Max Cl/Cd: 37.96 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor12-il-50000-n5.txt Download as CSV file: xf-hor12-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4182 0.11060 0.10300 -0.0197 1.0005 0.0818
-9.500 -0.4189 0.10590 0.09834 -0.0223 1.0005 0.0811
-9.250 -0.4183 0.10146 0.09394 -0.0246 1.0005 0.0809
-9.000 -0.4130 0.09810 0.09062 -0.0259 1.0005 0.0822
-8.750 -0.4098 0.09453 0.08710 -0.0276 1.0005 0.0837
-8.500 -0.4099 0.09052 0.08315 -0.0297 1.0005 0.0848
-8.250 -0.4130 0.08618 0.07888 -0.0320 1.0005 0.0855
-8.000 -0.4169 0.08136 0.07415 -0.0352 1.0005 0.0857
-7.750 -0.4200 0.07550 0.06835 -0.0403 1.0005 0.0860
-7.500 -0.4238 0.06759 0.06048 -0.0485 1.0005 0.0863
-7.250 -0.4296 0.05361 0.04621 -0.0653 1.0005 0.0879
-7.000 -0.4154 0.04300 0.03476 -0.0782 1.0005 0.0919
-6.750 -0.3965 0.04170 0.03350 -0.0781 1.0005 0.0947
-6.500 -0.3749 0.03864 0.03016 -0.0804 1.0005 0.0983
-6.250 -0.3494 0.03464 0.02552 -0.0840 1.0005 0.1036
-6.000 -0.3286 0.03316 0.02397 -0.0842 1.0005 0.1078
-5.750 -0.3077 0.03193 0.02260 -0.0845 1.0005 0.1145
-5.500 -0.2865 0.03074 0.02126 -0.0849 1.0005 0.1224
-5.250 -0.2650 0.02974 0.02004 -0.0852 1.0005 0.1318
-5.000 -0.2236 0.02887 0.01906 -0.0888 0.9910 0.1450
-4.750 -0.1791 0.02813 0.01807 -0.0931 0.9809 0.1638
-4.500 -0.1369 0.02758 0.01744 -0.0966 0.9701 0.1803
-4.250 -0.0944 0.02689 0.01662 -0.0999 0.9596 0.1957
-4.000 -0.0508 0.02621 0.01579 -0.1034 0.9501 0.2109
-3.750 -0.0086 0.02557 0.01508 -0.1064 0.9402 0.2255
-3.500 0.0294 0.02502 0.01448 -0.1085 0.9275 0.2404
-3.250 0.0665 0.02451 0.01390 -0.1104 0.9145 0.2554
-3.000 0.1027 0.02408 0.01341 -0.1120 0.9015 0.2726
-2.750 0.1382 0.02370 0.01298 -0.1133 0.8888 0.2905
-2.500 0.1729 0.02339 0.01264 -0.1143 0.8765 0.3101
-2.250 0.2045 0.02319 0.01244 -0.1148 0.8626 0.3298
-2.000 0.2350 0.02304 0.01227 -0.1150 0.8487 0.3518
-1.750 0.2652 0.02292 0.01213 -0.1151 0.8351 0.3749
-1.500 0.2946 0.02284 0.01205 -0.1150 0.8220 0.3990
-1.250 0.3242 0.02275 0.01191 -0.1148 0.8097 0.4249
-1.000 0.3529 0.02267 0.01181 -0.1145 0.7971 0.4516
-0.750 0.3805 0.02262 0.01178 -0.1141 0.7838 0.4788
-0.500 0.4082 0.02257 0.01172 -0.1136 0.7711 0.5076
-0.250 0.4357 0.02248 0.01164 -0.1131 0.7592 0.5377
0.000 0.4627 0.02236 0.01157 -0.1123 0.7477 0.5692
0.250 0.4884 0.02231 0.01163 -0.1116 0.7347 0.6024
0.500 0.5136 0.02222 0.01168 -0.1106 0.7226 0.6398
0.750 0.5377 0.02207 0.01169 -0.1091 0.7117 0.6867
1.000 0.5585 0.02185 0.01172 -0.1070 0.7002 0.7575
1.250 0.5794 0.02153 0.01160 -0.1049 0.6880 0.9995
1.500 0.6106 0.02184 0.01170 -0.1056 0.6766 0.9995
1.750 0.6410 0.02211 0.01178 -0.1059 0.6661 0.9995
2.000 0.6698 0.02250 0.01206 -0.1062 0.6537 0.9995
2.250 0.6985 0.02286 0.01233 -0.1063 0.6424 0.9995
2.500 0.7276 0.02312 0.01245 -0.1061 0.6326 0.9995
2.750 0.7552 0.02355 0.01284 -0.1061 0.6204 0.9995
3.000 0.7829 0.02396 0.01322 -0.1061 0.6091 0.9995
3.250 0.8113 0.02426 0.01343 -0.1058 0.5993 0.9995
3.500 0.8383 0.02471 0.01388 -0.1057 0.5877 0.9995
3.750 0.8652 0.02518 0.01436 -0.1055 0.5765 0.9995
4.000 0.8931 0.02551 0.01464 -0.1052 0.5668 0.9995
4.250 0.9195 0.02600 0.01516 -0.1049 0.5555 0.9995
4.500 0.9457 0.02651 0.01573 -0.1046 0.5443 0.9995
4.750 0.9732 0.02686 0.01605 -0.1042 0.5349 0.9995
5.000 0.9988 0.02740 0.01666 -0.1038 0.5234 0.9995
5.250 1.0242 0.02797 0.01730 -0.1034 0.5122 0.9995
5.500 1.0510 0.02835 0.01769 -0.1029 0.5024 0.9995
5.750 1.0762 0.02889 0.01830 -0.1024 0.4911 0.9995
6.250 1.1263 0.03000 0.01957 -0.1013 0.4694 0.9995
6.500 1.1511 0.03054 0.02020 -0.1007 0.4582 0.9995
6.750 1.1740 0.03127 0.02106 -0.1000 0.4463 0.9995
7.000 1.1978 0.03186 0.02176 -0.0993 0.4348 0.9995
7.250 1.2233 0.03223 0.02215 -0.0985 0.4241 0.9995
7.500 1.2447 0.03296 0.02304 -0.0976 0.4111 0.9995
7.750 1.2657 0.03369 0.02392 -0.0966 0.3980 0.9995
8.000 1.2866 0.03435 0.02472 -0.0955 0.3847 0.9995
8.250 1.3071 0.03495 0.02543 -0.0943 0.3709 0.9995
8.500 1.3262 0.03557 0.02615 -0.0929 0.3561 0.9995
8.750 1.3434 0.03624 0.02692 -0.0914 0.3402 0.9995
9.000 1.3581 0.03698 0.02778 -0.0897 0.3230 0.9995
9.250 1.3706 0.03781 0.02869 -0.0877 0.3049 0.9995
9.500 1.3807 0.03876 0.02970 -0.0856 0.2866 0.9995
9.750 1.3881 0.03988 0.03083 -0.0833 0.2685 0.9995
10.000 1.3912 0.04139 0.03241 -0.0809 0.2506 0.9995
10.250 1.3897 0.04313 0.03423 -0.0781 0.2339 0.9995
10.500 1.3857 0.04522 0.03635 -0.0756 0.2178 0.9995
10.750 1.3812 0.04770 0.03886 -0.0737 0.2022 0.9995
11.000 1.3765 0.05051 0.04170 -0.0724 0.1878 0.9995
11.250 1.3713 0.05363 0.04481 -0.0715 0.1749 0.9995
11.500 1.3654 0.05699 0.04816 -0.0708 0.1634 0.9995
11.750 1.3597 0.06064 0.05190 -0.0705 0.1521 0.9995
12.000 1.3542 0.06437 0.05566 -0.0702 0.1425 0.9995
12.250 1.3489 0.06800 0.05921 -0.0699 0.1348 0.9995
12.500 1.3438 0.07197 0.06333 -0.0700 0.1266 0.9995
13.000 1.3352 0.07965 0.07114 -0.0700 0.1139 0.9995
13.250 1.3328 0.08314 0.07459 -0.0700 0.1087 0.9995
13.500 1.3289 0.08721 0.07880 -0.0703 0.1039 0.9995
13.750 1.3255 0.09125 0.08299 -0.0708 0.0997 0.9995
14.000 1.3271 0.09433 0.08607 -0.0706 0.0962 0.9995
14.250 1.3270 0.09792 0.08975 -0.0707 0.0931 0.9995
14.500 1.3182 0.10338 0.09550 -0.0723 0.0905 0.9995
14.750 1.3095 0.10887 0.10121 -0.0741 0.0879 0.9995
15.000 1.3041 0.11372 0.10618 -0.0757 0.0854 0.9995
15.250 1.3174 0.11462 0.10697 -0.0745 0.0822 0.9995
15.500 1.2979 0.12283 0.11548 -0.0786 0.0810 0.9995
15.750 1.2705 0.13335 0.12630 -0.0847 0.0802 0.9995
16.000 1.2244 0.14986 0.14310 -0.0953 0.0800 0.9995
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