EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 500,000 Max Cl/Cd: 87.86 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2010-il-500000.txt Download as CSV file: xf-eh2010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.6291 0.03776 0.03470 -0.0187 1.0000 0.0157
-7.250 -0.6311 0.03014 0.02642 -0.0152 1.0000 0.0137
-7.000 -0.6212 0.02641 0.02223 -0.0129 1.0000 0.0139
-6.750 -0.6055 0.02398 0.01944 -0.0111 1.0000 0.0141
-6.500 -0.5871 0.02228 0.01746 -0.0095 1.0000 0.0144
-6.250 -0.5737 0.01874 0.01345 -0.0072 1.0000 0.0147
-6.000 -0.5564 0.01667 0.01117 -0.0054 1.0000 0.0157
-5.750 -0.5310 0.01594 0.01039 -0.0052 0.9974 0.0168
-5.500 -0.4928 0.01477 0.00908 -0.0074 0.9855 0.0180
-5.250 -0.4547 0.01372 0.00788 -0.0095 0.9678 0.0197
-5.000 -0.4168 0.01318 0.00722 -0.0114 0.9412 0.0212
-4.750 -0.3920 0.01179 0.00567 -0.0107 0.9047 0.0249
-4.500 -0.3684 0.01154 0.00528 -0.0095 0.8691 0.0281
-4.250 -0.3448 0.01130 0.00487 -0.0083 0.8373 0.0311
-4.000 -0.3218 0.01083 0.00427 -0.0072 0.8094 0.0365
-3.750 -0.2965 0.01071 0.00401 -0.0065 0.7843 0.0411
-3.500 -0.2724 0.01028 0.00352 -0.0056 0.7611 0.0509
-3.250 -0.2472 0.01002 0.00319 -0.0050 0.7404 0.0647
-3.000 -0.2215 0.00982 0.00294 -0.0045 0.7206 0.0801
-2.750 -0.1960 0.00959 0.00269 -0.0039 0.7027 0.0994
-2.500 -0.1702 0.00939 0.00250 -0.0035 0.6857 0.1239
-2.250 -0.1446 0.00914 0.00232 -0.0031 0.6694 0.1620
-2.000 -0.1202 0.00872 0.00215 -0.0026 0.6543 0.2403
-1.750 -0.1024 0.00757 0.00188 -0.0012 0.6406 0.4921
-1.500 -0.0872 0.00665 0.00183 0.0015 0.6279 0.7354
-1.250 -0.0636 0.00653 0.00185 0.0028 0.6149 0.8069
-1.000 -0.0383 0.00653 0.00186 0.0037 0.6022 0.8436
-0.750 -0.0128 0.00657 0.00187 0.0046 0.5897 0.8715
-0.500 0.0124 0.00663 0.00191 0.0056 0.5777 0.8968
-0.250 0.0383 0.00672 0.00197 0.0065 0.5662 0.9160
0.000 0.0651 0.00685 0.00203 0.0072 0.5550 0.9317
0.250 0.0937 0.00699 0.00210 0.0075 0.5439 0.9444
0.500 0.1237 0.00715 0.00217 0.0074 0.5329 0.9554
0.750 0.1664 0.00736 0.00230 0.0046 0.5208 0.9620
1.000 0.2096 0.00757 0.00243 0.0016 0.5090 0.9697
1.250 0.2507 0.00766 0.00245 -0.0012 0.4975 0.9719
1.500 0.2867 0.00774 0.00245 -0.0030 0.4870 0.9743
1.750 0.3210 0.00781 0.00245 -0.0045 0.4765 0.9774
2.000 0.3519 0.00788 0.00248 -0.0052 0.4663 0.9817
2.250 0.3879 0.00793 0.00248 -0.0070 0.4561 0.9836
2.500 0.4239 0.00800 0.00250 -0.0089 0.4460 0.9858
2.750 0.4591 0.00805 0.00252 -0.0106 0.4357 0.9884
3.000 0.4931 0.00812 0.00256 -0.0121 0.4258 0.9914
3.250 0.5266 0.00820 0.00261 -0.0134 0.4162 0.9941
3.500 0.5619 0.00827 0.00264 -0.0152 0.4062 0.9963
3.750 0.5971 0.00831 0.00269 -0.0170 0.3959 0.9988
4.000 0.6271 0.00838 0.00275 -0.0176 0.3867 1.0000
4.500 0.6730 0.00855 0.00293 -0.0160 0.3690 1.0000
4.750 0.6957 0.00866 0.00304 -0.0151 0.3603 1.0000
5.000 0.7184 0.00879 0.00316 -0.0142 0.3514 1.0000
5.250 0.7412 0.00890 0.00330 -0.0134 0.3422 1.0000
5.500 0.7637 0.00906 0.00347 -0.0125 0.3333 1.0000
5.750 0.7862 0.00922 0.00363 -0.0115 0.3236 1.0000
6.000 0.8088 0.00937 0.00379 -0.0106 0.3110 1.0000
6.250 0.8312 0.00955 0.00396 -0.0097 0.2971 1.0000
6.500 0.8538 0.00974 0.00416 -0.0088 0.2847 1.0000
6.750 0.8760 0.00997 0.00440 -0.0079 0.2691 1.0000
7.000 0.8981 0.01025 0.00463 -0.0069 0.2487 1.0000
7.250 0.9199 0.01057 0.00491 -0.0060 0.2280 1.0000
7.500 0.9413 0.01096 0.00523 -0.0050 0.2043 1.0000
7.750 0.9608 0.01156 0.00566 -0.0039 0.1680 1.0000
8.000 0.9781 0.01241 0.00626 -0.0025 0.1211 1.0000
8.250 0.9911 0.01371 0.00721 -0.0007 0.0624 1.0000
8.500 1.0030 0.01514 0.00838 0.0014 0.0235 1.0000
8.750 1.0185 0.01623 0.00952 0.0031 0.0152 1.0000
9.000 1.0352 0.01715 0.01051 0.0046 0.0123 1.0000
9.250 1.0464 0.01855 0.01208 0.0067 0.0106 1.0000
9.500 1.0635 0.01933 0.01294 0.0081 0.0096 1.0000
9.750 1.0792 0.02017 0.01385 0.0094 0.0088 1.0000
10.000 1.0932 0.02108 0.01483 0.0109 0.0081 1.0000
10.250 1.1020 0.02230 0.01614 0.0130 0.0078 1.0000
10.500 1.1034 0.02378 0.01772 0.0160 0.0074 1.0000
10.750 1.0950 0.02560 0.01968 0.0198 0.0072 1.0000
11.000 1.0853 0.02800 0.02222 0.0225 0.0070 1.0000
11.250 1.0887 0.02973 0.02406 0.0236 0.0068 1.0000
11.500 1.0860 0.03226 0.02670 0.0246 0.0069 1.0000
11.750 1.0906 0.03425 0.02880 0.0249 0.0067 1.0000
12.000 1.0923 0.03666 0.03133 0.0251 0.0066 1.0000
12.250 1.0938 0.03919 0.03398 0.0252 0.0065 1.0000
12.500 1.0950 0.04183 0.03674 0.0252 0.0064 1.0000
12.750 1.0943 0.04477 0.03981 0.0250 0.0063 1.0000
13.000 1.0933 0.04783 0.04300 0.0247 0.0061 1.0000
13.250 1.0908 0.05116 0.04647 0.0241 0.0060 1.0000
13.500 1.0871 0.05472 0.05019 0.0234 0.0060 1.0000
13.750 1.0822 0.05851 0.05412 0.0225 0.0062 1.0000
14.000 1.0745 0.06288 0.05866 0.0210 0.0061 1.0000
14.250 1.0659 0.06746 0.06340 0.0194 0.0062 1.0000
14.500 1.0553 0.07259 0.06869 0.0171 0.0061 1.0000
14.750 1.0441 0.07805 0.07431 0.0145 0.0062 1.0000
15.000 1.0313 0.08408 0.08050 0.0115 0.0062 1.0000
15.250 1.0174 0.09059 0.08717 0.0080 0.0061 1.0000
15.500 1.0025 0.09755 0.09428 0.0042 0.0063 1.0000
15.750 0.9883 0.10472 0.10159 0.0001 0.0063 1.0000
16.000 0.9702 0.11311 0.11014 -0.0047 0.0063 1.0000
16.250 0.9547 0.12125 0.11841 -0.0095 0.0064 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 2.0/10 (eh2010-il)