EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 50,000 Max Cl/Cd: 33.83 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2070-il-50000.txt Download as CSV file: xf-eh2070-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/7.0
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5556 0.10356 0.09746 0.0140 1.0000 0.1790
-7.750 -0.5427 0.09879 0.09271 0.0148 1.0000 0.1882
-7.500 -0.5616 0.09721 0.09128 0.0097 1.0000 0.1934
-7.250 -0.5513 0.09272 0.08684 0.0105 1.0000 0.2062
-7.000 -0.5438 0.08869 0.08286 0.0106 1.0000 0.2187
-6.750 -0.5430 0.08523 0.07946 0.0091 1.0000 0.2332
-6.500 -0.5436 0.08188 0.07609 0.0071 1.0000 0.2489
-6.250 -0.5289 0.07760 0.07187 0.0103 1.0000 0.2723
-6.000 -0.5221 0.07406 0.06839 0.0116 1.0000 0.2989
-5.750 -0.5163 0.07062 0.06503 0.0140 1.0000 0.3341
-4.750 -0.2977 0.05316 0.04717 0.0398 1.0000 0.8227
-4.500 -0.3559 0.05314 0.04743 0.0433 1.0000 0.7284
-4.250 -0.3996 0.05158 0.04622 0.0435 1.0000 0.6620
-3.750 -0.3372 0.03727 0.02904 -0.0130 1.0000 0.1465
-3.500 -0.3066 0.03409 0.02505 -0.0123 1.0000 0.1238
-3.250 -0.2801 0.03099 0.02153 -0.0115 1.0000 0.1160
-3.000 -0.2516 0.02876 0.01860 -0.0103 1.0000 0.1115
-2.750 -0.2262 0.02628 0.01599 -0.0095 1.0000 0.1176
-2.500 -0.1999 0.02438 0.01385 -0.0086 1.0000 0.1292
-2.250 -0.1704 0.02246 0.01169 -0.0077 1.0000 0.1403
-2.000 -0.0491 0.01504 0.00716 -0.0192 1.0000 1.0000
-1.750 -0.0278 0.01495 0.00654 -0.0181 1.0000 1.0000
-1.500 -0.0083 0.01490 0.00610 -0.0170 1.0000 1.0000
-1.250 0.0089 0.01491 0.00588 -0.0157 1.0000 1.0000
-1.000 0.0211 0.01502 0.00584 -0.0137 1.0000 1.0000
-0.750 0.0242 0.01531 0.00604 -0.0108 1.0000 1.0000
-0.500 0.0204 0.01581 0.00641 -0.0072 1.0000 1.0000
-0.250 0.0197 0.01638 0.00684 -0.0044 1.0000 1.0000
0.000 0.0379 0.01702 0.00729 -0.0052 0.9946 1.0000
0.250 0.1165 0.01767 0.00767 -0.0166 0.9667 1.0000
0.500 0.1969 0.01804 0.00791 -0.0276 0.9409 1.0000
0.750 0.2673 0.01823 0.00804 -0.0360 0.9149 1.0000
1.000 0.3177 0.01846 0.00822 -0.0402 0.8882 1.0000
1.250 0.3530 0.01880 0.00853 -0.0413 0.8622 1.0000
1.500 0.3798 0.01926 0.00894 -0.0407 0.8376 1.0000
1.750 0.4036 0.01975 0.00941 -0.0395 0.8152 1.0000
2.000 0.4264 0.02025 0.00994 -0.0381 0.7941 1.0000
2.250 0.4476 0.02086 0.01055 -0.0367 0.7732 1.0000
2.500 0.4689 0.02143 0.01113 -0.0350 0.7541 1.0000
2.750 0.4897 0.02206 0.01179 -0.0335 0.7354 1.0000
3.000 0.5104 0.02276 0.01254 -0.0320 0.7166 1.0000
3.250 0.5316 0.02339 0.01322 -0.0304 0.6994 1.0000
3.500 0.5527 0.02409 0.01408 -0.0289 0.6824 1.0000
3.750 0.5735 0.02494 0.01506 -0.0278 0.6641 1.0000
4.000 0.5948 0.02571 0.01595 -0.0264 0.6471 1.0000
4.250 0.6165 0.02644 0.01680 -0.0249 0.6308 1.0000
4.500 0.6378 0.02731 0.01783 -0.0236 0.6140 1.0000
4.750 0.6585 0.02836 0.01919 -0.0227 0.5961 1.0000
5.000 0.6799 0.02930 0.02034 -0.0214 0.5793 1.0000
5.250 0.7020 0.03008 0.02134 -0.0198 0.5627 1.0000
5.500 0.7224 0.03120 0.02274 -0.0187 0.5442 1.0000
5.750 0.7433 0.03214 0.02397 -0.0171 0.5250 1.0000
6.000 0.7664 0.03257 0.02468 -0.0148 0.5065 1.0000
6.250 0.7863 0.02707 0.01902 -0.0049 0.4377 1.0000
6.500 0.7913 0.02339 0.01483 0.0029 0.2595 1.0000
6.750 0.7942 0.02738 0.01722 0.0053 0.1229 1.0000
7.000 0.8083 0.03003 0.01969 0.0074 0.1015 1.0000
7.250 0.8261 0.03236 0.02200 0.0091 0.0874 1.0000
7.500 0.8473 0.03493 0.02453 0.0107 0.0783 1.0000
7.750 0.8729 0.03777 0.02768 0.0122 0.0749 1.0000
8.000 0.8961 0.04112 0.03141 0.0134 0.0733 1.0000
8.250 0.9147 0.04492 0.03572 0.0146 0.0734 1.0000
8.500 0.9277 0.04919 0.04056 0.0157 0.0745 1.0000
8.750 0.9354 0.05376 0.04564 0.0165 0.0759 1.0000
9.000 0.9390 0.05844 0.05073 0.0170 0.0772 1.0000
9.250 0.9382 0.06323 0.05586 0.0172 0.0782 1.0000
9.500 0.9357 0.06814 0.06099 0.0172 0.0793 1.0000
9.750 0.9364 0.07344 0.06641 0.0170 0.0802 1.0000
10.000 0.8788 0.07834 0.07178 0.0129 0.0840 1.0000
10.250 0.8468 0.08589 0.07936 0.0062 0.0855 1.0000
10.500 0.8217 0.09490 0.08833 -0.0012 0.0879 1.0000
10.750 0.8135 0.10212 0.09550 -0.0049 0.0909 1.0000
11.000 0.7960 0.11164 0.10493 -0.0117 0.0961 1.0000
11.250 0.7845 0.11982 0.11300 -0.0164 0.1026 1.0000
11.500 0.7736 0.12788 0.12098 -0.0216 0.1131 1.0000
11.750 0.6518 0.12612 0.11968 -0.0154 0.1108 1.0000
12.000 0.6411 0.13301 0.12653 -0.0191 0.1253 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 2.0/7.0 (eh2070-il)