EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 500,000 Max Cl/Cd: 62.34 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2510-il-500000-n5.txt Download as CSV file: xf-eh2510-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.5/10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5396 0.08905 0.08692 -0.0037 1.0000 0.0022
-9.500 -0.5447 0.08411 0.08200 -0.0065 1.0000 0.0022
-8.500 -0.7550 0.02413 0.01972 -0.0134 1.0000 0.0027
-8.250 -0.7393 0.02172 0.01694 -0.0119 1.0000 0.0027
-8.000 -0.7201 0.02012 0.01508 -0.0107 1.0000 0.0027
-7.750 -0.6992 0.01888 0.01364 -0.0097 1.0000 0.0026
-7.500 -0.6692 0.01773 0.01228 -0.0106 0.9696 0.0025
-7.250 -0.6263 0.01664 0.01095 -0.0141 0.9128 0.0024
-7.000 -0.6014 0.01604 0.01006 -0.0134 0.8619 0.0023
-6.750 -0.5787 0.01563 0.00950 -0.0123 0.8242 0.0019
-6.500 -0.5564 0.01490 0.00841 -0.0112 0.7930 0.0015
-6.250 -0.5334 0.01427 0.00774 -0.0104 0.7667 0.0048
-6.000 -0.5090 0.01388 0.00717 -0.0096 0.7425 0.0056
-5.750 -0.4843 0.01351 0.00663 -0.0090 0.7220 0.0063
-5.500 -0.4584 0.01340 0.00647 -0.0086 0.7028 0.0076
-5.250 -0.4317 0.01349 0.00653 -0.0085 0.6852 0.0097
-5.000 -0.4043 0.01373 0.00671 -0.0084 0.6687 0.0113
-4.750 -0.3773 0.01381 0.00672 -0.0082 0.6532 0.0118
-4.250 -0.3284 0.01253 0.00521 -0.0069 0.6259 0.0150
-4.000 -0.3028 0.01216 0.00474 -0.0064 0.6132 0.0157
-3.750 -0.2771 0.01183 0.00430 -0.0059 0.6009 0.0164
-3.500 -0.2513 0.01153 0.00390 -0.0054 0.5894 0.0170
-3.250 -0.2253 0.01126 0.00353 -0.0050 0.5785 0.0176
-3.000 -0.1992 0.01104 0.00321 -0.0045 0.5677 0.0181
-2.750 -0.1727 0.01085 0.00295 -0.0042 0.5571 0.0190
-2.500 -0.1462 0.01066 0.00267 -0.0038 0.5474 0.0201
-2.250 -0.1198 0.01047 0.00240 -0.0034 0.5378 0.0228
-2.000 -0.0945 0.01041 0.00217 -0.0028 0.4954 0.0290
-1.750 -0.0690 0.01027 0.00200 -0.0024 0.4675 0.0508
-1.500 -0.0423 0.01014 0.00188 -0.0021 0.4585 0.0675
-1.250 -0.0159 0.00999 0.00178 -0.0019 0.4520 0.0903
-1.000 0.0100 0.01002 0.00167 -0.0015 0.4133 0.1079
-0.750 0.0365 0.00992 0.00159 -0.0013 0.4011 0.1321
-0.500 0.0625 0.00974 0.00153 -0.0010 0.3923 0.1785
-0.250 0.0812 0.00871 0.00137 0.0003 0.3851 0.4522
0.000 0.0913 0.00750 0.00138 0.0040 0.3788 0.7950
0.250 0.1159 0.00745 0.00143 0.0050 0.3706 0.8476
0.500 0.1425 0.00745 0.00147 0.0056 0.3641 0.8759
0.750 0.1698 0.00750 0.00152 0.0060 0.3563 0.9016
1.000 0.1980 0.00757 0.00158 0.0061 0.3497 0.9222
1.250 0.2284 0.00767 0.00165 0.0058 0.3428 0.9382
1.500 0.2611 0.00778 0.00173 0.0049 0.3366 0.9520
1.750 0.2963 0.00789 0.00179 0.0034 0.3300 0.9572
2.000 0.3272 0.00798 0.00183 0.0027 0.3239 0.9610
2.250 0.3554 0.00820 0.00190 0.0025 0.2947 0.9662
2.500 0.3885 0.00842 0.00199 0.0012 0.2710 0.9682
2.750 0.4199 0.00890 0.00216 0.0000 0.2138 0.9706
3.000 0.4452 0.01046 0.00291 -0.0007 0.0130 0.9744
3.250 0.4755 0.01064 0.00304 -0.0013 0.0103 0.9777
3.500 0.5058 0.01080 0.00320 -0.0021 0.0097 0.9806
3.750 0.5384 0.01097 0.00335 -0.0033 0.0094 0.9824
4.000 0.5704 0.01115 0.00352 -0.0044 0.0093 0.9846
4.250 0.6018 0.01134 0.00370 -0.0053 0.0092 0.9872
4.500 0.6324 0.01154 0.00390 -0.0062 0.0091 0.9900
4.750 0.6623 0.01176 0.00414 -0.0069 0.0090 0.9928
5.000 0.6941 0.01197 0.00436 -0.0080 0.0089 0.9950
5.250 0.7255 0.01221 0.00461 -0.0091 0.0088 0.9973
5.500 0.7568 0.01246 0.00488 -0.0101 0.0088 0.9993
5.750 0.7822 0.01271 0.00516 -0.0099 0.0088 1.0000
6.000 0.8034 0.01297 0.00544 -0.0089 0.0088 1.0000
6.250 0.8247 0.01325 0.00578 -0.0078 0.0087 1.0000
6.500 0.8459 0.01357 0.00613 -0.0068 0.0085 1.0000
6.750 0.8669 0.01394 0.00654 -0.0057 0.0081 1.0000
7.000 0.8882 0.01429 0.00692 -0.0048 0.0079 1.0000
7.250 0.9093 0.01467 0.00735 -0.0038 0.0077 1.0000
7.500 0.9294 0.01516 0.00788 -0.0027 0.0072 1.0000
7.750 0.9484 0.01578 0.00857 -0.0015 0.0068 1.0000
8.000 0.9671 0.01641 0.00925 -0.0003 0.0064 1.0000
8.250 0.9835 0.01723 0.01016 0.0011 0.0060 1.0000
8.500 0.9981 0.01818 0.01118 0.0027 0.0054 1.0000
8.750 1.0321 0.01736 0.01045 0.0022 0.0038 1.0000
9.000 1.0486 0.01814 0.01129 0.0035 0.0034 1.0000
9.250 1.0648 0.01891 0.01212 0.0049 0.0032 1.0000
9.500 1.0797 0.01974 0.01304 0.0064 0.0031 1.0000
9.750 1.0930 0.02064 0.01403 0.0080 0.0030 1.0000
10.000 1.1026 0.02174 0.01523 0.0101 0.0028 1.0000
10.250 1.1117 0.02276 0.01634 0.0121 0.0028 1.0000
10.500 1.1164 0.02376 0.01746 0.0148 0.0028 1.0000
10.750 1.1151 0.02510 0.01890 0.0177 0.0027 1.0000
11.000 1.1130 0.02687 0.02078 0.0195 0.0027 1.0000
11.250 1.1136 0.02887 0.02288 0.0203 0.0027 1.0000
11.500 1.1150 0.03111 0.02523 0.0204 0.0026 1.0000
11.750 1.1158 0.03364 0.02786 0.0202 0.0026 1.0000
12.000 1.1171 0.03624 0.03057 0.0198 0.0026 1.0000
12.250 1.1167 0.03912 0.03355 0.0192 0.0026 1.0000
12.500 1.1160 0.04207 0.03660 0.0186 0.0026 1.0000
12.750 1.1131 0.04533 0.03997 0.0179 0.0026 1.0000
13.000 1.1126 0.04835 0.04307 0.0172 0.0026 1.0000
13.250 1.1099 0.05165 0.04647 0.0164 0.0025 1.0000
13.500 1.1070 0.05500 0.04992 0.0155 0.0026 1.0000
13.750 1.1032 0.05849 0.05352 0.0146 0.0025 1.0000
14.000 1.1000 0.06197 0.05709 0.0136 0.0025 1.0000
14.250 1.0965 0.06559 0.06081 0.0125 0.0025 1.0000
14.500 1.0926 0.06939 0.06472 0.0113 0.0025 1.0000
14.750 1.0891 0.07326 0.06868 0.0100 0.0025 1.0000
15.000 1.0855 0.07725 0.07278 0.0085 0.0025 1.0000
15.250 1.0805 0.08151 0.07714 0.0070 0.0025 1.0000
15.500 1.0751 0.08593 0.08168 0.0053 0.0025 1.0000
15.750 1.0699 0.09048 0.08634 0.0035 0.0025 1.0000
16.000 1.0646 0.09513 0.09112 0.0015 0.0025 1.0000
16.250 1.0592 0.09992 0.09602 -0.0006 0.0025 1.0000
16.500 1.0521 0.10509 0.10131 -0.0029 0.0025 1.0000
16.750 1.0445 0.11055 0.10688 -0.0054 0.0025 1.0000
17.000 1.0370 0.11606 0.11251 -0.0081 0.0025 1.0000
17.250 1.0303 0.12157 0.11812 -0.0108 0.0025 1.0000
17.500 1.0204 0.12793 0.12461 -0.0140 0.0025 1.0000
17.750 1.0118 0.13412 0.13091 -0.0173 0.0025 1.0000
18.000 1.0025 0.14067 0.13758 -0.0208 0.0025 1.0000
18.250 0.9927 0.14755 0.14458 -0.0245 0.0025 1.0000
18.500 0.9844 0.15429 0.15141 -0.0282 0.0026 1.0000
18.750 0.9752 0.16145 0.15867 -0.0323 0.0026 1.0000
19.000 0.9643 0.16934 0.16667 -0.0367 0.0026 1.0000
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Polar data table (+)
Polar graphs
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