EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 500,000 Max Cl/Cd: 77.95 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh3012-il-500000-n5.txt Download as CSV file: xf-eh3012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 3.0/12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -1.0039 0.03561 0.03168 -0.0296 1.0000 0.0003
-12.000 -1.0044 0.03264 0.02843 -0.0273 1.0000 0.0003
-11.750 -0.9982 0.03037 0.02591 -0.0253 1.0000 0.0003
-11.500 -0.9875 0.02857 0.02391 -0.0236 1.0000 0.0003
-11.250 -0.9747 0.02695 0.02208 -0.0220 1.0000 0.0003
-11.000 -0.9594 0.02557 0.02053 -0.0205 1.0000 0.0004
-10.750 -0.9427 0.02433 0.01913 -0.0192 1.0000 0.0004
-10.500 -0.9242 0.02331 0.01797 -0.0180 1.0000 0.0004
-10.250 -0.9047 0.02237 0.01690 -0.0169 1.0000 0.0004
-10.000 -0.8846 0.02150 0.01591 -0.0159 1.0000 0.0004
-9.750 -0.8638 0.02071 0.01502 -0.0149 1.0000 0.0005
-9.500 -0.8364 0.01987 0.01407 -0.0153 0.9791 0.0005
-9.250 -0.7982 0.01907 0.01307 -0.0178 0.9059 0.0005
-9.000 -0.7777 0.01859 0.01235 -0.0163 0.8535 0.0005
-8.750 -0.7567 0.01813 0.01168 -0.0150 0.8160 0.0005
-8.500 -0.7346 0.01768 0.01104 -0.0139 0.7857 0.0005
-8.250 -0.7118 0.01724 0.01042 -0.0130 0.7599 0.0005
-8.000 -0.6881 0.01682 0.00985 -0.0123 0.7419 0.0005
-7.750 -0.6639 0.01642 0.00932 -0.0116 0.7233 0.0005
-7.500 -0.6394 0.01604 0.00881 -0.0110 0.7082 0.0005
-7.250 -0.6146 0.01567 0.00833 -0.0104 0.6923 0.0006
-7.000 -0.5897 0.01534 0.00788 -0.0099 0.6768 0.0006
-6.250 -0.5053 0.01703 0.00968 -0.0102 0.6321 0.0007
-6.000 -0.4875 0.01432 0.00653 -0.0081 0.6211 0.0008
-5.750 -0.4648 0.01334 0.00551 -0.0071 0.6104 0.0074
-5.500 -0.4391 0.01307 0.00522 -0.0066 0.6006 0.0099
-5.250 -0.4130 0.01286 0.00494 -0.0063 0.5906 0.0113
-5.000 -0.3869 0.01264 0.00467 -0.0059 0.5811 0.0118
-4.750 -0.3609 0.01244 0.00440 -0.0055 0.5715 0.0124
-4.500 -0.3346 0.01224 0.00417 -0.0051 0.5620 0.0130
-4.250 -0.3083 0.01207 0.00394 -0.0047 0.5533 0.0137
-4.000 -0.2819 0.01190 0.00372 -0.0044 0.5443 0.0144
-3.750 -0.2555 0.01174 0.00351 -0.0041 0.5361 0.0155
-3.500 -0.2291 0.01157 0.00331 -0.0037 0.5279 0.0174
-3.250 -0.2027 0.01142 0.00313 -0.0034 0.5201 0.0199
-3.000 -0.1762 0.01127 0.00295 -0.0031 0.5117 0.0224
-2.750 -0.1496 0.01113 0.00279 -0.0027 0.5046 0.0254
-2.500 -0.1231 0.01100 0.00264 -0.0024 0.4971 0.0296
-2.250 -0.0968 0.01085 0.00251 -0.0021 0.4901 0.0401
-2.000 -0.0702 0.01072 0.00240 -0.0018 0.4827 0.0516
-1.750 -0.0437 0.01062 0.00231 -0.0015 0.4762 0.0612
-1.500 -0.0169 0.01050 0.00222 -0.0013 0.4695 0.0718
-1.250 0.0096 0.01040 0.00214 -0.0010 0.4624 0.0866
-1.000 0.0358 0.01024 0.00208 -0.0007 0.4561 0.1161
-0.750 0.0616 0.01005 0.00203 -0.0004 0.4497 0.1559
-0.500 0.0863 0.00977 0.00196 0.0001 0.4439 0.2255
-0.250 0.1069 0.00907 0.00182 0.0012 0.4378 0.3991
0.000 0.1142 0.00777 0.00176 0.0053 0.4326 0.7498
0.250 0.1388 0.00770 0.00181 0.0063 0.4272 0.8021
0.500 0.1652 0.00769 0.00184 0.0068 0.4212 0.8309
0.750 0.1917 0.00772 0.00188 0.0073 0.4150 0.8551
1.000 0.2188 0.00775 0.00194 0.0077 0.4095 0.8769
1.250 0.2465 0.00781 0.00200 0.0079 0.4038 0.8950
1.750 0.3024 0.00800 0.00211 0.0082 0.3860 0.9220
2.000 0.3325 0.00814 0.00218 0.0079 0.3709 0.9321
2.250 0.3634 0.00826 0.00225 0.0073 0.3630 0.9406
2.500 0.3944 0.00837 0.00232 0.0066 0.3557 0.9459
2.750 0.4221 0.00847 0.00237 0.0066 0.3493 0.9512
3.000 0.4541 0.00857 0.00244 0.0057 0.3425 0.9538
3.250 0.4863 0.00871 0.00252 0.0047 0.3322 0.9563
3.500 0.5175 0.00887 0.00260 0.0038 0.3189 0.9594
3.750 0.5473 0.00906 0.00270 0.0032 0.3029 0.9632
4.000 0.5761 0.00916 0.00279 0.0030 0.2996 0.9672
4.250 0.6094 0.00930 0.00292 0.0017 0.2935 0.9688
4.500 0.6426 0.00945 0.00304 0.0003 0.2858 0.9705
4.750 0.6748 0.00964 0.00318 -0.0008 0.2757 0.9726
5.000 0.7059 0.00987 0.00334 -0.0018 0.2605 0.9753
5.250 0.7358 0.01006 0.00351 -0.0024 0.2502 0.9787
5.500 0.7656 0.01029 0.00369 -0.0031 0.2378 0.9815
5.750 0.7976 0.01056 0.00390 -0.0044 0.2237 0.9833
6.000 0.8290 0.01082 0.00413 -0.0055 0.2115 0.9855
6.250 0.8587 0.01125 0.00444 -0.0064 0.1882 0.9884
6.500 0.8894 0.01141 0.00463 -0.0072 0.1873 0.9911
6.750 0.9179 0.01187 0.00499 -0.0080 0.1644 0.9936
7.000 0.9478 0.01238 0.00540 -0.0091 0.1425 0.9960
7.250 0.9623 0.01508 0.00736 -0.0092 0.0092 1.0000
7.500 0.9797 0.01543 0.00772 -0.0075 0.0082 1.0000
7.750 0.9974 0.01578 0.00810 -0.0060 0.0077 1.0000
8.250 1.0327 0.01651 0.00890 -0.0029 0.0072 1.0000
8.500 1.0503 0.01690 0.00933 -0.0014 0.0064 1.0000
8.750 1.0670 0.01735 0.00982 0.0002 0.0059 1.0000
9.000 1.0829 0.01786 0.01036 0.0018 0.0057 1.0000
9.250 1.0993 0.01832 0.01089 0.0034 0.0058 1.0000
9.500 1.1136 0.01888 0.01150 0.0052 0.0056 1.0000
9.750 1.1259 0.01952 0.01219 0.0072 0.0054 1.0000
10.000 1.1342 0.02034 0.01306 0.0097 0.0050 1.0000
10.250 1.1389 0.02107 0.01386 0.0128 0.0049 1.0000
10.500 1.1433 0.02189 0.01474 0.0156 0.0049 1.0000
10.750 1.1494 0.02282 0.01576 0.0176 0.0048 1.0000
11.000 1.1537 0.02411 0.01714 0.0192 0.0048 1.0000
11.250 1.1592 0.02554 0.01867 0.0202 0.0043 1.0000
11.500 1.1635 0.02730 0.02052 0.0207 0.0041 1.0000
11.750 1.1685 0.02917 0.02247 0.0209 0.0037 1.0000
12.000 1.1704 0.03149 0.02488 0.0209 0.0039 1.0000
12.250 1.1725 0.03392 0.02741 0.0207 0.0036 1.0000
12.750 1.1736 0.03929 0.03302 0.0199 0.0030 1.0000
13.000 1.1707 0.04242 0.03621 0.0194 0.0034 1.0000
13.250 1.1646 0.04600 0.03994 0.0187 0.0029 1.0000
13.500 1.1642 0.04891 0.04290 0.0181 0.0032 1.0000
13.750 1.1543 0.05302 0.04716 0.0171 0.0028 1.0000
14.000 1.1466 0.05689 0.05112 0.0162 0.0027 1.0000
15.000 1.1229 0.07268 0.06726 0.0117 0.0027 1.0000
15.250 1.1204 0.07630 0.07093 0.0105 0.0026 1.0000
15.500 1.1140 0.08062 0.07536 0.0091 0.0027 1.0000
15.750 1.1126 0.08416 0.07895 0.0080 0.0026 1.0000
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Polar data table (+)
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