EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 200,000 Max Cl/Cd: 65.32 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh3012-il-200000-n5.txt Download as CSV file: xf-eh3012-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5057 0.09350 0.09008 -0.0092 1.0000 0.0130
-10.250 -0.7278 0.05105 0.04735 -0.0294 1.0000 0.0115
-10.000 -0.7735 0.04024 0.03586 -0.0268 1.0000 0.0113
-9.750 -0.7853 0.03459 0.02955 -0.0240 1.0000 0.0115
-9.500 -0.7724 0.03303 0.02786 -0.0226 1.0000 0.0117
-9.250 -0.7541 0.03232 0.02711 -0.0217 1.0000 0.0122
-9.000 -0.7414 0.03035 0.02488 -0.0202 1.0000 0.0124
-8.750 -0.7265 0.02863 0.02291 -0.0187 1.0000 0.0126
-8.500 -0.7100 0.02710 0.02115 -0.0174 1.0000 0.0130
-8.250 -0.6927 0.02562 0.01942 -0.0160 1.0000 0.0132
-8.000 -0.6666 0.02414 0.01768 -0.0164 0.9705 0.0137
-7.750 -0.6301 0.02278 0.01600 -0.0187 0.9174 0.0144
-7.500 -0.6006 0.02177 0.01467 -0.0191 0.8739 0.0151
-7.250 -0.5775 0.02115 0.01386 -0.0182 0.8377 0.0157
-7.000 -0.5551 0.02058 0.01311 -0.0172 0.8081 0.0162
-6.750 -0.5323 0.02002 0.01234 -0.0162 0.7832 0.0169
-6.500 -0.5096 0.01938 0.01149 -0.0152 0.7617 0.0176
-6.250 -0.4863 0.01879 0.01067 -0.0142 0.7441 0.0181
-6.000 -0.4625 0.01824 0.00994 -0.0134 0.7260 0.0188
-5.750 -0.4384 0.01781 0.00940 -0.0127 0.7100 0.0202
-5.500 -0.4141 0.01737 0.00881 -0.0120 0.6944 0.0213
-5.250 -0.3895 0.01695 0.00826 -0.0113 0.6801 0.0228
-5.000 -0.3649 0.01658 0.00779 -0.0107 0.6664 0.0253
-4.750 -0.3398 0.01626 0.00737 -0.0102 0.6534 0.0282
-4.500 -0.3148 0.01593 0.00700 -0.0096 0.6412 0.0321
-4.250 -0.2895 0.01563 0.00661 -0.0091 0.6300 0.0362
-3.750 -0.2398 0.01489 0.00579 -0.0078 0.6090 0.0466
-3.500 -0.2146 0.01460 0.00546 -0.0072 0.5992 0.0552
-3.250 -0.1894 0.01437 0.00518 -0.0067 0.5892 0.0664
-3.000 -0.1637 0.01416 0.00494 -0.0062 0.5796 0.0778
-2.750 -0.1383 0.01397 0.00471 -0.0057 0.5709 0.0895
-2.500 -0.1128 0.01376 0.00450 -0.0052 0.5616 0.1017
-2.250 -0.0875 0.01358 0.00431 -0.0047 0.5535 0.1171
-2.000 -0.0620 0.01339 0.00412 -0.0043 0.5448 0.1356
-1.750 -0.0370 0.01318 0.00393 -0.0037 0.5370 0.1551
-1.500 -0.0120 0.01296 0.00375 -0.0032 0.5290 0.1829
-1.250 0.0116 0.01263 0.00357 -0.0024 0.5220 0.2358
-1.000 0.0216 0.01121 0.00331 0.0006 0.5151 0.5388
-0.750 0.0389 0.01058 0.00356 0.0037 0.5086 0.7890
-0.500 0.0678 0.01064 0.00367 0.0041 0.5009 0.8424
-0.250 0.0980 0.01078 0.00374 0.0042 0.4939 0.8739
0.000 0.1319 0.01094 0.00385 0.0035 0.4864 0.8964
0.250 0.1661 0.01113 0.00394 0.0026 0.4790 0.9139
0.500 0.2031 0.01133 0.00406 0.0012 0.4719 0.9280
0.750 0.2401 0.01153 0.00416 -0.0004 0.4645 0.9396
1.000 0.2827 0.01175 0.00427 -0.0031 0.4572 0.9488
1.250 0.3217 0.01188 0.00432 -0.0053 0.4498 0.9550
1.500 0.3558 0.01197 0.00431 -0.0067 0.4435 0.9581
1.750 0.3871 0.01202 0.00432 -0.0075 0.4365 0.9617
2.000 0.4141 0.01211 0.00433 -0.0075 0.4306 0.9665
2.250 0.4475 0.01217 0.00435 -0.0088 0.4243 0.9688
2.500 0.4808 0.01224 0.00437 -0.0101 0.4176 0.9714
2.750 0.5126 0.01233 0.00441 -0.0111 0.4118 0.9746
3.000 0.5428 0.01242 0.00450 -0.0118 0.4054 0.9784
3.500 0.6067 0.01258 0.00458 -0.0139 0.3884 0.9844
3.750 0.6385 0.01267 0.00462 -0.0150 0.3799 0.9875
4.000 0.6695 0.01277 0.00472 -0.0159 0.3707 0.9908
4.250 0.7009 0.01289 0.00483 -0.0169 0.3645 0.9938
4.500 0.7337 0.01299 0.00494 -0.0182 0.3577 0.9967
4.750 0.7661 0.01313 0.00508 -0.0195 0.3526 0.9996
5.000 0.7898 0.01326 0.00526 -0.0189 0.3470 1.0000
5.250 0.8112 0.01341 0.00543 -0.0179 0.3415 1.0000
5.500 0.8323 0.01360 0.00560 -0.0169 0.3369 1.0000
5.750 0.8539 0.01376 0.00583 -0.0159 0.3315 1.0000
6.000 0.8752 0.01395 0.00607 -0.0148 0.3261 1.0000
6.500 0.9173 0.01435 0.00655 -0.0127 0.3140 1.0000
6.750 0.9376 0.01459 0.00677 -0.0115 0.3062 1.0000
7.000 0.9586 0.01480 0.00706 -0.0104 0.2971 1.0000
7.250 0.9789 0.01507 0.00733 -0.0093 0.2891 1.0000
7.500 0.9996 0.01532 0.00764 -0.0082 0.2806 1.0000
7.750 1.0197 0.01561 0.00796 -0.0070 0.2704 1.0000
8.000 1.0393 0.01595 0.00831 -0.0058 0.2613 1.0000
8.250 1.0595 0.01626 0.00869 -0.0047 0.2509 1.0000
8.500 1.0790 0.01663 0.00910 -0.0035 0.2410 1.0000
8.750 1.0972 0.01706 0.00954 -0.0022 0.2268 1.0000
9.000 1.1138 0.01759 0.01006 -0.0008 0.2083 1.0000
9.250 1.1281 0.01827 0.01066 0.0010 0.1863 1.0000
9.500 1.1385 0.01919 0.01145 0.0031 0.1565 1.0000
9.750 1.1411 0.02059 0.01260 0.0059 0.1162 1.0000
10.000 1.1276 0.02284 0.01446 0.0105 0.0623 1.0000
10.500 1.0975 0.02696 0.01832 0.0187 0.0186 1.0000
10.750 1.0973 0.02872 0.02015 0.0201 0.0163 1.0000
11.000 1.0962 0.03084 0.02235 0.0210 0.0145 1.0000
11.250 1.0969 0.03300 0.02465 0.0214 0.0134 1.0000
11.500 1.0973 0.03537 0.02713 0.0215 0.0129 1.0000
11.750 1.0967 0.03796 0.02983 0.0215 0.0126 1.0000
12.000 1.0956 0.04069 0.03267 0.0212 0.0120 1.0000
12.250 1.0919 0.04380 0.03591 0.0208 0.0114 1.0000
12.500 1.0911 0.04664 0.03885 0.0204 0.0114 1.0000
12.750 1.0849 0.05018 0.04253 0.0197 0.0112 1.0000
13.000 1.0788 0.05379 0.04623 0.0189 0.0106 1.0000
13.250 1.0735 0.05736 0.04993 0.0180 0.0107 1.0000
13.500 1.0676 0.06109 0.05375 0.0171 0.0104 1.0000
13.750 1.0606 0.06511 0.05792 0.0159 0.0103 1.0000
14.000 1.0527 0.06943 0.06236 0.0145 0.0103 1.0000
14.250 1.0490 0.07325 0.06628 0.0133 0.0100 1.0000
14.500 1.0421 0.07765 0.07080 0.0118 0.0099 1.0000
14.750 1.0319 0.08262 0.07587 0.0100 0.0094 1.0000
15.000 1.0277 0.08676 0.08012 0.0085 0.0094 1.0000
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Polar data table (+)
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