EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 100,000 Max Cl/Cd: 39.56 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh3012-il-100000.txt Download as CSV file: xf-eh3012-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4152 0.10732 0.10281 -0.0109 1.0000 0.0933
-9.250 -0.4348 0.10436 0.09996 -0.0177 1.0000 0.0940
-9.000 -0.4591 0.10106 0.09673 -0.0234 1.0000 0.0943
-8.750 -0.4018 0.09517 0.09083 -0.0141 1.0000 0.0977
-8.500 -0.3943 0.09187 0.08757 -0.0145 1.0000 0.1004
-8.250 -0.3943 0.08838 0.08415 -0.0165 1.0000 0.1035
-8.000 -0.4089 0.08440 0.08028 -0.0215 1.0000 0.1066
-7.750 -0.4428 0.08200 0.07785 -0.0259 1.0000 0.1086
-7.500 -0.4497 0.07755 0.07339 -0.0271 1.0000 0.1100
-7.250 -0.4238 0.07321 0.06925 -0.0252 1.0000 0.1128
-7.000 -0.4168 0.07022 0.06632 -0.0251 1.0000 0.1164
-6.750 -0.4238 0.06771 0.06381 -0.0258 1.0000 0.1217
-6.500 -0.4245 0.06403 0.06003 -0.0292 0.9823 0.1262
-6.250 -0.3928 0.06048 0.05607 -0.0358 0.9547 0.1405
-6.000 -0.3544 0.05512 0.05095 -0.0384 0.9331 0.1474
-5.750 -0.3347 0.05159 0.04714 -0.0404 0.9053 0.1598
-5.500 -0.3225 0.04924 0.04447 -0.0397 0.8798 0.1735
-5.250 -0.3069 0.04663 0.04179 -0.0381 0.8564 0.1806
-5.000 -0.2867 0.03588 0.02914 -0.0356 0.8432 0.0779
-4.750 -0.2690 0.03306 0.02593 -0.0336 0.8254 0.0755
-4.500 -0.2492 0.03089 0.02328 -0.0316 0.8090 0.0766
-4.250 -0.2277 0.02888 0.02076 -0.0297 0.7937 0.0778
-4.000 -0.2042 0.02699 0.01840 -0.0280 0.7794 0.0787
-3.750 -0.1798 0.02521 0.01628 -0.0267 0.7658 0.0821
-3.500 -0.1553 0.02423 0.01519 -0.0257 0.7526 0.0891
-3.250 -0.1284 0.02296 0.01357 -0.0245 0.7403 0.0953
-3.000 -0.1027 0.02203 0.01260 -0.0237 0.7271 0.1078
-2.750 -0.0769 0.02102 0.01157 -0.0229 0.7148 0.1251
-2.500 -0.0527 0.02018 0.01085 -0.0220 0.7038 0.1510
-2.250 -0.0294 0.01944 0.01019 -0.0208 0.6936 0.1827
-2.000 -0.0069 0.01875 0.00970 -0.0196 0.6822 0.2209
-1.750 0.0119 0.01773 0.00914 -0.0178 0.6729 0.2987
-1.500 0.2346 0.01751 0.01018 -0.0461 0.6512 0.9977
-1.250 0.2618 0.01748 0.00993 -0.0464 0.6413 1.0000
-1.000 0.2830 0.01751 0.00977 -0.0455 0.6319 1.0000
-0.750 0.3048 0.01760 0.00974 -0.0448 0.6220 1.0000
-0.500 0.3260 0.01766 0.00959 -0.0437 0.6144 1.0000
-0.250 0.3480 0.01778 0.00964 -0.0431 0.6042 1.0000
0.000 0.3697 0.01788 0.00958 -0.0422 0.5969 1.0000
0.250 0.3917 0.01803 0.00968 -0.0415 0.5877 1.0000
0.500 0.4136 0.01817 0.00968 -0.0406 0.5805 1.0000
0.750 0.4355 0.01834 0.00979 -0.0399 0.5716 1.0000
1.000 0.4573 0.01850 0.00985 -0.0390 0.5644 1.0000
1.250 0.4792 0.01870 0.01000 -0.0382 0.5560 1.0000
1.500 0.5010 0.01890 0.01010 -0.0372 0.5494 1.0000
1.750 0.5225 0.01916 0.01037 -0.0364 0.5411 1.0000
2.000 0.5445 0.01934 0.01040 -0.0354 0.5357 1.0000
2.250 0.5653 0.01973 0.01087 -0.0346 0.5269 1.0000
2.500 0.5872 0.01990 0.01091 -0.0335 0.5212 1.0000
2.750 0.6075 0.02036 0.01145 -0.0327 0.5131 1.0000
3.000 0.6291 0.02059 0.01161 -0.0316 0.5071 1.0000
3.250 0.6494 0.02105 0.01211 -0.0306 0.5001 1.0000
3.500 0.6703 0.02136 0.01241 -0.0295 0.4933 1.0000
3.750 0.6918 0.02168 0.01266 -0.0284 0.4878 1.0000
4.000 0.7107 0.02224 0.01333 -0.0273 0.4801 1.0000
4.250 0.7332 0.02243 0.01342 -0.0262 0.4750 1.0000
4.500 0.7509 0.02316 0.01428 -0.0251 0.4675 1.0000
4.750 0.7720 0.02352 0.01463 -0.0239 0.4619 1.0000
5.000 0.7928 0.02399 0.01510 -0.0228 0.4566 1.0000
5.250 0.8105 0.02467 0.01591 -0.0216 0.4492 1.0000
5.500 0.8341 0.02485 0.01601 -0.0206 0.4444 1.0000
5.750 0.8494 0.02580 0.01713 -0.0192 0.4369 1.0000
6.000 0.8713 0.02614 0.01748 -0.0182 0.4313 1.0000
6.250 0.8922 0.02666 0.01801 -0.0171 0.4260 1.0000
6.500 0.9074 0.02766 0.01919 -0.0157 0.4189 1.0000
6.750 0.9320 0.02786 0.01934 -0.0149 0.4144 1.0000
7.000 0.9450 0.02908 0.02077 -0.0134 0.4074 1.0000
7.250 0.9662 0.02953 0.02126 -0.0124 0.4015 1.0000
7.500 0.9939 0.02958 0.02123 -0.0118 0.3973 1.0000
7.750 0.9992 0.03132 0.02328 -0.0098 0.3891 1.0000
8.000 1.0282 0.03109 0.02301 -0.0093 0.3841 1.0000
8.250 1.0364 0.03261 0.02475 -0.0074 0.3766 1.0000
8.500 1.0679 0.03180 0.02386 -0.0069 0.3695 1.0000
8.750 1.0811 0.03256 0.02479 -0.0053 0.3609 1.0000
9.000 1.1151 0.03156 0.02367 -0.0050 0.3538 1.0000
9.250 1.1242 0.03275 0.02509 -0.0031 0.3459 1.0000
9.500 1.1560 0.03206 0.02433 -0.0028 0.3391 1.0000
9.750 1.1651 0.03314 0.02565 -0.0009 0.3311 1.0000
10.000 1.1980 0.03231 0.02474 -0.0007 0.3239 1.0000
10.250 1.2048 0.03347 0.02615 0.0014 0.3160 1.0000
10.500 1.2370 0.03280 0.02542 0.0015 0.3091 1.0000
10.750 1.2427 0.03375 0.02663 0.0038 0.3004 1.0000
11.000 1.2694 0.03292 0.02576 0.0046 0.2908 1.0000
11.250 1.2811 0.03337 0.02637 0.0064 0.2825 1.0000
11.500 1.2930 0.03355 0.02667 0.0084 0.2732 1.0000
11.750 1.3089 0.03309 0.02620 0.0101 0.2623 1.0000
12.000 1.3125 0.03335 0.02658 0.0128 0.2517 1.0000
12.250 1.3037 0.03447 0.02788 0.0164 0.2434 1.0000
12.500 1.3057 0.03507 0.02851 0.0187 0.2346 1.0000
12.750 1.2926 0.03710 0.03074 0.0208 0.2260 1.0000
13.000 1.2836 0.03928 0.03304 0.0218 0.2169 1.0000
13.250 1.2756 0.04167 0.03548 0.0222 0.2069 1.0000
13.500 1.2570 0.04570 0.03968 0.0216 0.1971 1.0000
13.750 1.2374 0.05026 0.04435 0.0205 0.1860 1.0000
14.000 1.2199 0.05489 0.04904 0.0192 0.1757 1.0000
14.250 1.1966 0.06051 0.05469 0.0174 0.1634 1.0000
14.500 1.1726 0.06645 0.06064 0.0153 0.1500 1.0000
14.750 1.1498 0.07259 0.06676 0.0130 0.1357 1.0000
15.000 1.1275 0.07886 0.07292 0.0107 0.1199 1.0000
15.250 1.1049 0.08536 0.07922 0.0082 0.1046 1.0000
15.500 1.0871 0.09130 0.08501 0.0061 0.0932 1.0000
15.750 1.0741 0.09665 0.09026 0.0042 0.0842 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 3.0/12 (eh3012-il)