ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 50,000 Max Cl/Cd: 43.72 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor07-il-50000.txt Download as CSV file: xf-hor07-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3898 0.10436 0.09779 -0.0059 1.0000 0.1644
-7.250 -0.3877 0.10233 0.09584 -0.0080 1.0000 0.1704
-7.000 -0.3848 0.10034 0.09396 -0.0134 1.0000 0.1737
-6.750 -0.3689 0.09522 0.08885 -0.0106 1.0000 0.1795
-6.500 -0.3628 0.09432 0.08802 -0.0191 1.0000 0.1875
-6.250 -0.3499 0.08900 0.08275 -0.0160 1.0000 0.1917
-6.000 -0.3373 0.08716 0.08095 -0.0228 1.0000 0.2024
-5.750 -0.3258 0.08244 0.07631 -0.0196 1.0000 0.2087
-5.500 -0.3118 0.07971 0.07361 -0.0250 1.0000 0.2197
-5.250 -0.2945 0.07728 0.07120 -0.0304 1.0000 0.2331
-5.000 -0.2864 0.07305 0.06709 -0.0257 1.0000 0.2398
-4.750 -0.2730 0.07015 0.06425 -0.0286 1.0000 0.2512
-4.500 -0.2604 0.06762 0.06177 -0.0311 1.0000 0.2645
-4.250 -0.2499 0.06535 0.05954 -0.0326 1.0000 0.2787
-4.000 -0.2486 0.06284 0.05713 -0.0291 1.0000 0.2868
-3.750 -0.2416 0.06062 0.05496 -0.0291 1.0000 0.3004
-3.500 -0.2274 0.05853 0.05284 -0.0319 1.0000 0.3232
-3.250 -0.2223 0.05613 0.05049 -0.0294 1.0000 0.3409
-2.750 -0.0959 0.04539 0.03876 -0.0608 1.0000 0.2221
-2.500 -0.0167 0.03683 0.02893 -0.0758 1.0000 0.1538
-2.250 0.0244 0.03360 0.02489 -0.0803 1.0000 0.1577
-2.000 0.0505 0.03210 0.02329 -0.0813 1.0000 0.1689
-1.750 0.0834 0.03048 0.02123 -0.0834 1.0000 0.1852
-1.500 0.1107 0.02959 0.02021 -0.0844 1.0000 0.2102
-1.250 0.1399 0.02876 0.01914 -0.0857 1.0000 0.2441
-1.000 0.1677 0.02810 0.01838 -0.0868 1.0000 0.2886
-0.750 0.2149 0.02732 0.01751 -0.0912 0.9925 0.3595
-0.500 0.2692 0.02664 0.01675 -0.0967 0.9819 0.4285
-0.250 0.3232 0.02594 0.01616 -0.1020 0.9704 0.4981
0.000 0.3688 0.02431 0.01560 -0.1053 0.9587 0.6836
0.250 0.4201 0.02431 0.01506 -0.1101 0.9416 1.0000
0.500 0.4704 0.02467 0.01503 -0.1147 0.9265 1.0000
0.750 0.5185 0.02502 0.01512 -0.1187 0.9117 1.0000
1.000 0.5603 0.02542 0.01536 -0.1215 0.8969 1.0000
1.250 0.5985 0.02588 0.01572 -0.1234 0.8823 1.0000
1.500 0.6335 0.02641 0.01617 -0.1248 0.8677 1.0000
1.750 0.6659 0.02702 0.01673 -0.1257 0.8533 1.0000
2.000 0.6960 0.02770 0.01741 -0.1261 0.8389 1.0000
2.250 0.7242 0.02846 0.01816 -0.1262 0.8247 1.0000
2.500 0.7507 0.02932 0.01904 -0.1262 0.8110 1.0000
2.750 0.7763 0.03029 0.02004 -0.1262 0.7982 1.0000
3.000 0.8024 0.03125 0.02108 -0.1261 0.7861 1.0000
3.250 0.8327 0.03190 0.02178 -0.1261 0.7757 1.0000
3.500 0.8542 0.03316 0.02312 -0.1257 0.7626 1.0000
3.750 0.8744 0.03460 0.02466 -0.1254 0.7502 1.0000
4.000 0.8954 0.03604 0.02625 -0.1252 0.7388 1.0000
4.250 0.9217 0.03698 0.02731 -0.1248 0.7284 1.0000
4.500 0.9471 0.03780 0.02827 -0.1239 0.7164 1.0000
4.750 0.9664 0.03916 0.02978 -0.1231 0.7029 1.0000
5.000 0.9844 0.04072 0.03151 -0.1224 0.6900 1.0000
5.250 1.0034 0.04220 0.03322 -0.1216 0.6778 1.0000
5.500 1.0265 0.04291 0.03414 -0.1201 0.6634 1.0000
5.750 1.0647 0.03981 0.03122 -0.1145 0.6376 1.0000
6.000 1.0978 0.03521 0.02674 -0.1064 0.6007 1.0000
6.250 1.1262 0.03149 0.02302 -0.0996 0.5648 1.0000
6.500 1.1481 0.02884 0.02049 -0.0939 0.5190 1.0000
6.750 1.1590 0.02651 0.01791 -0.0866 0.4001 1.0000
7.000 1.1556 0.02947 0.01912 -0.0819 0.2124 1.0000
7.250 1.1626 0.03252 0.02156 -0.0795 0.1799 1.0000
7.500 1.1790 0.03482 0.02376 -0.0773 0.1624 1.0000
7.750 1.2019 0.03677 0.02568 -0.0758 0.1498 1.0000
8.000 1.2282 0.03883 0.02763 -0.0747 0.1391 1.0000
8.250 1.2607 0.04133 0.02996 -0.0744 0.1315 1.0000
8.500 1.2899 0.04406 0.03307 -0.0737 0.1277 1.0000
8.750 1.3157 0.04711 0.03653 -0.0728 0.1248 1.0000
9.000 1.3409 0.05049 0.03999 -0.0723 0.1197 1.0000
9.250 1.3578 0.05427 0.04426 -0.0710 0.1170 1.0000
9.500 1.3720 0.05848 0.04904 -0.0694 0.1166 1.0000
9.750 1.3799 0.06298 0.05413 -0.0676 0.1164 1.0000
10.000 1.3792 0.06755 0.05933 -0.0655 0.1156 1.0000
10.250 1.3729 0.07232 0.06461 -0.0635 0.1152 1.0000
10.500 1.3620 0.07735 0.07005 -0.0616 0.1155 1.0000
10.750 1.3489 0.08262 0.07565 -0.0600 0.1165 1.0000
11.000 1.3402 0.08831 0.08154 -0.0590 0.1179 1.0000
11.250 1.3041 0.09283 0.08635 -0.0573 0.1197 1.0000
11.500 1.2251 0.10259 0.09635 -0.0627 0.1275 1.0000
11.750 1.2069 0.11043 0.10424 -0.0657 0.1297 1.0000
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Polar data table (+)
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