EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 200,000 Max Cl/Cd: 63.06 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2012-il-200000-n5.txt Download as CSV file: xf-eh2012-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7360 0.05783 0.05415 -0.0339 1.0000 0.0140
-11.000 -0.7659 0.05155 0.04764 -0.0366 1.0000 0.0138
-10.750 -0.7951 0.04660 0.04241 -0.0357 1.0000 0.0137
-10.500 -0.8144 0.04312 0.03866 -0.0328 1.0000 0.0138
-10.250 -0.8260 0.03988 0.03506 -0.0298 1.0000 0.0141
-10.000 -0.8297 0.03675 0.03152 -0.0272 1.0000 0.0145
-9.750 -0.8262 0.03412 0.02847 -0.0249 1.0000 0.0148
-9.500 -0.8186 0.03178 0.02585 -0.0230 1.0000 0.0152
-9.250 -0.8061 0.03003 0.02392 -0.0214 1.0000 0.0156
-9.000 -0.7912 0.02851 0.02224 -0.0199 1.0000 0.0160
-8.750 -0.7749 0.02713 0.02069 -0.0185 1.0000 0.0165
-8.500 -0.7576 0.02578 0.01917 -0.0172 1.0000 0.0171
-8.250 -0.7395 0.02445 0.01766 -0.0158 1.0000 0.0178
-8.000 -0.7207 0.02320 0.01623 -0.0145 1.0000 0.0185
-7.750 -0.7013 0.02206 0.01489 -0.0131 1.0000 0.0194
-7.500 -0.6829 0.02101 0.01376 -0.0117 1.0000 0.0205
-7.250 -0.6633 0.02034 0.01307 -0.0105 1.0000 0.0219
-7.000 -0.6438 0.01969 0.01235 -0.0091 0.9999 0.0237
-6.750 -0.6089 0.01869 0.01121 -0.0109 0.9809 0.0260
-6.500 -0.5747 0.01783 0.01033 -0.0126 0.9583 0.0288
-6.250 -0.5397 0.01718 0.00954 -0.0142 0.9337 0.0327
-6.000 -0.5077 0.01651 0.00884 -0.0152 0.9073 0.0375
-5.750 -0.4790 0.01604 0.00822 -0.0152 0.8798 0.0424
-5.500 -0.4539 0.01557 0.00770 -0.0146 0.8535 0.0487
-5.250 -0.4298 0.01519 0.00719 -0.0137 0.8286 0.0549
-5.000 -0.4060 0.01487 0.00678 -0.0127 0.8063 0.0625
-4.750 -0.3824 0.01454 0.00638 -0.0118 0.7849 0.0704
-4.500 -0.3582 0.01428 0.00600 -0.0109 0.7654 0.0792
-4.000 -0.3100 0.01371 0.00531 -0.0093 0.7301 0.1007
-3.750 -0.2855 0.01345 0.00500 -0.0086 0.7138 0.1140
-3.500 -0.2609 0.01320 0.00471 -0.0080 0.6981 0.1302
-3.250 -0.2362 0.01295 0.00443 -0.0073 0.6836 0.1498
-3.000 -0.2118 0.01267 0.00418 -0.0066 0.6696 0.1769
-2.750 -0.1878 0.01237 0.00393 -0.0059 0.6563 0.2130
-2.500 -0.1645 0.01196 0.00370 -0.0052 0.6435 0.2702
-2.250 -0.1437 0.01136 0.00345 -0.0040 0.6311 0.3708
-2.000 -0.1273 0.01053 0.00328 -0.0019 0.6198 0.5381
-1.750 -0.1080 0.01008 0.00331 0.0002 0.6088 0.6738
-1.500 -0.0836 0.00999 0.00336 0.0015 0.5976 0.7434
-1.250 -0.0574 0.01001 0.00340 0.0024 0.5862 0.7852
-1.000 -0.0306 0.01007 0.00343 0.0031 0.5754 0.8149
-0.750 -0.0038 0.01016 0.00346 0.0037 0.5651 0.8391
-0.500 0.0231 0.01029 0.00353 0.0045 0.5547 0.8645
-0.250 0.0528 0.01046 0.00366 0.0048 0.5444 0.8866
0.000 0.0830 0.01068 0.00380 0.0049 0.5347 0.9071
0.250 0.1169 0.01090 0.00393 0.0043 0.5244 0.9216
0.500 0.1488 0.01100 0.00395 0.0036 0.5145 0.9288
0.750 0.1815 0.01109 0.00393 0.0027 0.5051 0.9331
1.000 0.2102 0.01115 0.00392 0.0025 0.4957 0.9393
1.250 0.2429 0.01123 0.00393 0.0015 0.4865 0.9432
1.500 0.2769 0.01133 0.00394 0.0002 0.4775 0.9466
1.750 0.3091 0.01140 0.00396 -0.0007 0.4678 0.9511
2.000 0.3385 0.01149 0.00399 -0.0011 0.4594 0.9564
2.250 0.3741 0.01158 0.00403 -0.0028 0.4502 0.9589
2.500 0.4080 0.01166 0.00408 -0.0042 0.4412 0.9622
2.750 0.4392 0.01177 0.00412 -0.0050 0.4330 0.9667
3.000 0.4703 0.01186 0.00421 -0.0058 0.4241 0.9709
3.250 0.5048 0.01196 0.00428 -0.0073 0.4157 0.9738
3.500 0.5376 0.01206 0.00436 -0.0085 0.4070 0.9774
3.750 0.5683 0.01218 0.00448 -0.0093 0.3985 0.9818
4.000 0.6014 0.01230 0.00457 -0.0106 0.3902 0.9849
4.250 0.6349 0.01240 0.00470 -0.0120 0.3814 0.9881
4.500 0.6670 0.01255 0.00484 -0.0131 0.3733 0.9918
4.750 0.6995 0.01268 0.00500 -0.0143 0.3645 0.9951
5.000 0.7325 0.01282 0.00515 -0.0157 0.3561 0.9984
5.250 0.7598 0.01299 0.00534 -0.0159 0.3479 1.0000
5.500 0.7811 0.01316 0.00555 -0.0148 0.3407 1.0000
5.750 0.8020 0.01335 0.00575 -0.0137 0.3333 1.0000
6.000 0.8230 0.01354 0.00599 -0.0125 0.3256 1.0000
6.250 0.8435 0.01377 0.00624 -0.0113 0.3179 1.0000
6.500 0.8644 0.01398 0.00651 -0.0102 0.3099 1.0000
6.750 0.8846 0.01424 0.00677 -0.0089 0.3023 1.0000
7.000 0.9056 0.01447 0.00708 -0.0078 0.2938 1.0000
7.250 0.9258 0.01476 0.00740 -0.0065 0.2862 1.0000
7.500 0.9463 0.01503 0.00774 -0.0053 0.2772 1.0000
7.750 0.9667 0.01533 0.00809 -0.0041 0.2688 1.0000
8.000 0.9864 0.01567 0.00845 -0.0029 0.2596 1.0000
8.250 1.0068 0.01598 0.00884 -0.0017 0.2496 1.0000
8.500 1.0263 0.01634 0.00927 -0.0005 0.2384 1.0000
8.750 1.0445 0.01675 0.00968 0.0009 0.2220 1.0000
9.000 1.0610 0.01729 0.01014 0.0024 0.1996 1.0000
9.250 1.0767 0.01792 0.01070 0.0040 0.1763 1.0000
9.500 1.0923 0.01859 0.01133 0.0055 0.1560 1.0000
9.750 1.1064 0.01936 0.01206 0.0071 0.1361 1.0000
10.000 1.1184 0.02027 0.01290 0.0090 0.1137 1.0000
10.250 1.1275 0.02134 0.01387 0.0111 0.0921 1.0000
10.500 1.1325 0.02261 0.01503 0.0135 0.0698 1.0000
10.750 1.1322 0.02398 0.01630 0.0167 0.0512 1.0000
11.000 1.1286 0.02547 0.01774 0.0199 0.0388 1.0000
11.500 1.1267 0.02883 0.02118 0.0239 0.0273 1.0000
11.750 1.1238 0.03102 0.02343 0.0250 0.0242 1.0000
12.000 1.1230 0.03328 0.02580 0.0256 0.0223 1.0000
12.250 1.1217 0.03579 0.02843 0.0257 0.0208 1.0000
12.500 1.1184 0.03866 0.03142 0.0256 0.0195 1.0000
12.750 1.1131 0.04192 0.03478 0.0251 0.0186 1.0000
13.250 1.1025 0.04882 0.04192 0.0235 0.0170 1.0000
13.500 1.0976 0.05238 0.04561 0.0225 0.0165 1.0000
13.750 1.0912 0.05621 0.04956 0.0214 0.0157 1.0000
14.000 1.0849 0.06011 0.05357 0.0201 0.0154 1.0000
14.250 1.0773 0.06428 0.05785 0.0187 0.0149 1.0000
14.500 1.0701 0.06856 0.06223 0.0171 0.0146 1.0000
14.750 1.0623 0.07307 0.06684 0.0153 0.0143 1.0000
15.000 1.0543 0.07772 0.07158 0.0135 0.0140 1.0000
15.250 1.0473 0.08230 0.07625 0.0116 0.0138 1.0000
15.500 1.0395 0.08707 0.08109 0.0097 0.0135 1.0000
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Polar data table (+)
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