EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 500,000 Max Cl/Cd: 93.45 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh3012-il-500000.txt Download as CSV file: xf-eh3012-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3526 0.09788 0.09595 -0.0105 1.0000 0.0238
-10.000 -0.3534 0.09313 0.09122 -0.0126 1.0000 0.0238
-9.750 -0.3617 0.08662 0.08474 -0.0147 1.0000 0.0242
-9.500 -0.3604 0.08265 0.08078 -0.0157 1.0000 0.0244
-9.250 -0.3567 0.07933 0.07748 -0.0165 1.0000 0.0247
-9.000 -0.3493 0.07498 0.07313 -0.0193 0.9430 0.0250
-8.500 -0.4839 0.06721 0.06518 -0.0301 1.0000 0.0242
-8.250 -0.4873 0.06360 0.06153 -0.0303 0.9796 0.0243
-8.000 -0.4633 0.06075 0.05843 -0.0343 0.8692 0.0248
-7.750 -0.4635 0.05838 0.05579 -0.0328 0.8185 0.0251
-7.000 -0.5121 0.03050 0.02609 -0.0243 0.7592 0.0199
-6.750 -0.5012 0.02669 0.02176 -0.0218 0.7415 0.0185
-6.500 -0.4861 0.02403 0.01860 -0.0198 0.7248 0.0186
-6.250 -0.4674 0.02194 0.01608 -0.0182 0.7089 0.0188
-6.000 -0.4461 0.02030 0.01408 -0.0169 0.6938 0.0189
-5.750 -0.4228 0.01901 0.01248 -0.0159 0.6796 0.0191
-5.500 -0.3996 0.01722 0.01039 -0.0149 0.6667 0.0194
-5.250 -0.3755 0.01591 0.00893 -0.0142 0.6542 0.0200
-5.000 -0.3503 0.01525 0.00817 -0.0136 0.6418 0.0208
-4.500 -0.2992 0.01412 0.00683 -0.0124 0.6187 0.0227
-4.250 -0.2732 0.01371 0.00630 -0.0119 0.6087 0.0237
-4.000 -0.2495 0.01295 0.00547 -0.0110 0.5991 0.0256
-3.750 -0.2235 0.01263 0.00512 -0.0105 0.5893 0.0276
-3.500 -0.1977 0.01234 0.00474 -0.0099 0.5800 0.0294
-3.250 -0.1733 0.01181 0.00418 -0.0091 0.5710 0.0321
-3.000 -0.1471 0.01159 0.00391 -0.0087 0.5625 0.0357
-2.750 -0.1217 0.01128 0.00358 -0.0081 0.5538 0.0414
-2.500 -0.0959 0.01099 0.00331 -0.0075 0.5456 0.0535
-2.250 -0.0703 0.01076 0.00312 -0.0070 0.5377 0.0738
-2.000 -0.0437 0.01060 0.00298 -0.0066 0.5297 0.0889
-1.750 -0.0174 0.01048 0.00284 -0.0063 0.5221 0.1034
-1.500 0.0092 0.01033 0.00272 -0.0059 0.5147 0.1220
-1.250 0.0351 0.01015 0.00261 -0.0055 0.5077 0.1507
-1.000 0.0600 0.00985 0.00251 -0.0050 0.5011 0.2105
-0.750 0.0645 0.00797 0.00226 -0.0010 0.4954 0.6646
-0.500 0.0819 0.00762 0.00237 0.0018 0.4894 0.8180
-0.250 0.1071 0.00760 0.00243 0.0028 0.4822 0.8612
0.000 0.1337 0.00767 0.00247 0.0035 0.4754 0.8858
0.250 0.1606 0.00774 0.00253 0.0042 0.4689 0.9059
0.500 0.1882 0.00784 0.00259 0.0046 0.4624 0.9222
0.750 0.2187 0.00800 0.00268 0.0045 0.4564 0.9344
1.000 0.2514 0.00814 0.00279 0.0038 0.4497 0.9451
1.500 0.3270 0.00852 0.00304 0.0002 0.4363 0.9596
1.750 0.3717 0.00874 0.00316 -0.0031 0.4297 0.9635
2.000 0.4045 0.00888 0.00326 -0.0040 0.4236 0.9700
2.250 0.4471 0.00900 0.00331 -0.0071 0.4165 0.9718
2.500 0.4842 0.00910 0.00335 -0.0091 0.4103 0.9738
2.750 0.5190 0.00915 0.00338 -0.0107 0.4041 0.9761
3.000 0.5517 0.00927 0.00342 -0.0118 0.3983 0.9790
3.250 0.5813 0.00935 0.00351 -0.0123 0.3930 0.9830
3.500 0.6176 0.00941 0.00354 -0.0142 0.3871 0.9844
3.750 0.6528 0.00951 0.00358 -0.0159 0.3809 0.9863
4.000 0.6876 0.00954 0.00361 -0.0176 0.3725 0.9886
4.250 0.7213 0.00962 0.00365 -0.0190 0.3637 0.9913
4.500 0.7538 0.00970 0.00372 -0.0202 0.3566 0.9940
4.750 0.7888 0.00977 0.00377 -0.0219 0.3487 0.9958
5.000 0.8235 0.00984 0.00382 -0.0236 0.3415 0.9980
5.250 0.8581 0.00994 0.00391 -0.0253 0.3347 1.0000
5.500 0.8802 0.01002 0.00400 -0.0244 0.3282 1.0000
5.750 0.9017 0.01016 0.00411 -0.0234 0.3218 1.0000
6.000 0.9237 0.01024 0.00423 -0.0224 0.3151 1.0000
6.250 0.9448 0.01041 0.00437 -0.0213 0.3091 1.0000
6.500 0.9666 0.01053 0.00453 -0.0203 0.3030 1.0000
6.750 0.9878 0.01070 0.00469 -0.0193 0.2965 1.0000
7.000 1.0091 0.01086 0.00486 -0.0182 0.2887 1.0000
7.250 1.0299 0.01107 0.00505 -0.0171 0.2804 1.0000
7.500 1.0513 0.01125 0.00526 -0.0160 0.2715 1.0000
7.750 1.0719 0.01150 0.00548 -0.0149 0.2629 1.0000
8.000 1.0931 0.01171 0.00572 -0.0138 0.2545 1.0000
8.250 1.1140 0.01197 0.00598 -0.0127 0.2463 1.0000
8.500 1.1339 0.01231 0.00627 -0.0116 0.2314 1.0000
8.750 1.1535 0.01268 0.00661 -0.0103 0.2175 1.0000
9.000 1.1725 0.01310 0.00698 -0.0091 0.2021 1.0000
9.250 1.1895 0.01367 0.00746 -0.0076 0.1818 1.0000
9.500 1.2030 0.01447 0.00810 -0.0057 0.1529 1.0000
9.750 1.2101 0.01568 0.00905 -0.0030 0.1122 1.0000
10.000 1.2113 0.01717 0.01028 0.0004 0.0711 1.0000
10.250 1.2006 0.01917 0.01200 0.0051 0.0290 1.0000
10.500 1.2062 0.02002 0.01286 0.0080 0.0250 1.0000
10.750 1.2109 0.02081 0.01371 0.0110 0.0237 1.0000
11.000 1.2147 0.02183 0.01480 0.0134 0.0226 1.0000
11.250 1.2199 0.02300 0.01604 0.0152 0.0220 1.0000
11.500 1.2224 0.02459 0.01772 0.0165 0.0211 1.0000
11.750 1.2264 0.02631 0.01953 0.0173 0.0207 1.0000
12.000 1.2303 0.02825 0.02155 0.0176 0.0204 1.0000
12.250 1.2323 0.03051 0.02393 0.0177 0.0203 1.0000
12.500 1.2357 0.03273 0.02625 0.0177 0.0199 1.0000
12.750 1.2357 0.03541 0.02902 0.0174 0.0194 1.0000
13.000 1.2352 0.03819 0.03190 0.0171 0.0190 1.0000
13.250 1.2338 0.04111 0.03491 0.0166 0.0190 1.0000
13.500 1.2291 0.04445 0.03835 0.0160 0.0187 1.0000
13.750 1.2236 0.04794 0.04194 0.0154 0.0183 1.0000
14.000 1.2179 0.05148 0.04558 0.0147 0.0186 1.0000
14.250 1.2092 0.05544 0.04965 0.0138 0.0186 1.0000
14.500 1.2016 0.05935 0.05365 0.0129 0.0183 1.0000
14.750 1.1954 0.06325 0.05763 0.0118 0.0179 1.0000
15.000 1.1887 0.06727 0.06174 0.0107 0.0178 1.0000
15.250 1.1806 0.07157 0.06612 0.0094 0.0177 1.0000
15.500 1.1738 0.07578 0.07042 0.0081 0.0176 1.0000
15.750 1.1674 0.07995 0.07468 0.0068 0.0175 1.0000
16.000 1.1606 0.08427 0.07907 0.0055 0.0173 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 3.0/12 (eh3012-il)