EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.29 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2510-il-1000000-n5.txt Download as CSV file: xf-eh2510-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5495 0.11150 0.10982 0.0074 1.0000 0.0028
-11.000 -0.5509 0.10665 0.10498 0.0052 1.0000 0.0028
-10.000 -0.8981 0.02520 0.02182 -0.0163 1.0000 0.0035
-9.750 -0.8841 0.02300 0.01935 -0.0148 1.0000 0.0035
-9.500 -0.8668 0.02139 0.01753 -0.0135 1.0000 0.0034
-9.250 -0.8479 0.02000 0.01595 -0.0123 1.0000 0.0034
-9.000 -0.8273 0.01890 0.01469 -0.0113 1.0000 0.0034
-8.750 -0.8061 0.01785 0.01348 -0.0104 0.9994 0.0034
-8.500 -0.7607 0.01659 0.01192 -0.0147 0.9171 0.0033
-8.250 -0.7404 0.01593 0.01092 -0.0132 0.8581 0.0032
-8.000 -0.7188 0.01533 0.01008 -0.0120 0.8201 0.0031
-7.750 -0.6959 0.01480 0.00934 -0.0111 0.7879 0.0030
-7.500 -0.6722 0.01431 0.00865 -0.0104 0.7605 0.0030
-7.250 -0.6480 0.01386 0.00804 -0.0097 0.7371 0.0029
-7.000 -0.6233 0.01343 0.00747 -0.0091 0.7154 0.0029
-6.750 -0.5984 0.01304 0.00693 -0.0085 0.6957 0.0028
-6.500 -0.5731 0.01267 0.00644 -0.0080 0.6786 0.0028
-6.250 -0.5476 0.01232 0.00598 -0.0076 0.6628 0.0027
-6.000 -0.5219 0.01200 0.00556 -0.0071 0.6482 0.0027
-5.750 -0.4961 0.01171 0.00517 -0.0067 0.6334 0.0025
-5.500 -0.4701 0.01144 0.00481 -0.0063 0.6196 0.0024
-5.000 -0.4195 0.01061 0.00386 -0.0053 0.5948 0.0047
-4.750 -0.3931 0.01041 0.00361 -0.0049 0.5831 0.0060
-4.500 -0.3664 0.01029 0.00352 -0.0047 0.5716 0.0087
-3.500 -0.2585 0.00989 0.00299 -0.0040 0.5312 0.0128
-3.250 -0.2321 0.00965 0.00267 -0.0036 0.5221 0.0134
-3.000 -0.2054 0.00947 0.00241 -0.0033 0.5126 0.0138
-2.750 -0.1785 0.00931 0.00220 -0.0030 0.5041 0.0143
-2.500 -0.1516 0.00918 0.00200 -0.0027 0.4953 0.0148
-2.250 -0.1259 0.00925 0.00182 -0.0023 0.4356 0.0155
-2.000 -0.0991 0.00918 0.00167 -0.0020 0.4184 0.0166
-1.750 -0.0718 0.00908 0.00154 -0.0018 0.4138 0.0177
-1.500 -0.0456 0.00917 0.00144 -0.0015 0.3702 0.0200
-1.250 -0.0190 0.00900 0.00134 -0.0013 0.3632 0.0423
-1.000 0.0078 0.00889 0.00127 -0.0011 0.3566 0.0608
-0.750 0.0350 0.00880 0.00121 -0.0009 0.3525 0.0757
-0.500 0.0622 0.00871 0.00117 -0.0007 0.3476 0.0949
-0.250 0.0893 0.00861 0.00113 -0.0006 0.3446 0.1181
0.000 0.1162 0.00851 0.00110 -0.0004 0.3407 0.1522
0.250 0.1420 0.00824 0.00108 -0.0001 0.3370 0.2359
0.500 0.1530 0.00659 0.00094 0.0027 0.3350 0.7174
0.750 0.1761 0.00636 0.00099 0.0039 0.3304 0.7967
1.000 0.2015 0.00629 0.00103 0.0045 0.3280 0.8385
1.250 0.2273 0.00629 0.00108 0.0051 0.3185 0.8680
1.500 0.2531 0.00640 0.00115 0.0056 0.2981 0.8889
1.750 0.2785 0.00662 0.00125 0.0061 0.2622 0.9083
2.000 0.3043 0.00686 0.00138 0.0066 0.2289 0.9276
2.250 0.3242 0.00825 0.00202 0.0075 0.0102 0.9422
2.500 0.3528 0.00838 0.00212 0.0073 0.0085 0.9490
2.750 0.3824 0.00851 0.00222 0.0069 0.0082 0.9542
3.000 0.4129 0.00864 0.00234 0.0063 0.0080 0.9587
3.250 0.4421 0.00879 0.00246 0.0059 0.0079 0.9639
3.500 0.4729 0.00894 0.00260 0.0052 0.0079 0.9675
3.750 0.5051 0.00911 0.00276 0.0041 0.0078 0.9701
4.000 0.5369 0.00928 0.00291 0.0031 0.0079 0.9728
4.250 0.5676 0.00946 0.00308 0.0023 0.0079 0.9758
4.500 0.5970 0.00964 0.00325 0.0018 0.0080 0.9793
4.750 0.6287 0.00984 0.00345 0.0008 0.0080 0.9811
5.000 0.6603 0.01005 0.00367 -0.0003 0.0081 0.9828
5.250 0.6913 0.01028 0.00390 -0.0012 0.0081 0.9849
5.500 0.7215 0.01051 0.00414 -0.0020 0.0081 0.9873
5.750 0.7512 0.01077 0.00441 -0.0026 0.0079 0.9901
6.000 0.7797 0.01108 0.00472 -0.0031 0.0076 0.9927
6.250 0.8101 0.01144 0.00510 -0.0040 0.0072 0.9947
7.250 0.9218 0.01293 0.00676 -0.0058 0.0032 1.0000
7.500 0.9420 0.01336 0.00721 -0.0046 0.0030 1.0000
7.750 0.9625 0.01379 0.00769 -0.0035 0.0027 1.0000
8.000 0.9827 0.01425 0.00822 -0.0024 0.0026 1.0000
8.250 1.0028 0.01474 0.00875 -0.0013 0.0024 1.0000
8.500 1.0221 0.01530 0.00937 -0.0001 0.0021 1.0000
8.750 1.0408 0.01589 0.01004 0.0011 0.0020 1.0000
9.000 1.0588 0.01653 0.01074 0.0024 0.0019 1.0000
9.250 1.0754 0.01725 0.01154 0.0039 0.0018 1.0000
9.500 1.0904 0.01806 0.01243 0.0055 0.0017 1.0000
9.750 1.1035 0.01897 0.01343 0.0073 0.0017 1.0000
10.000 1.1161 0.01986 0.01440 0.0091 0.0016 1.0000
10.250 1.1280 0.02072 0.01536 0.0109 0.0016 1.0000
10.500 1.1372 0.02167 0.01639 0.0130 0.0016 1.0000
10.750 1.1401 0.02261 0.01741 0.0162 0.0016 1.0000
11.000 1.1426 0.02375 0.01863 0.0187 0.0016 1.0000
11.250 1.1452 0.02522 0.02019 0.0202 0.0016 1.0000
11.500 1.1482 0.02704 0.02210 0.0209 0.0015 1.0000
11.750 1.1515 0.02914 0.02430 0.0210 0.0015 1.0000
12.000 1.1551 0.03143 0.02668 0.0207 0.0015 1.0000
12.250 1.1570 0.03404 0.02939 0.0202 0.0015 1.0000
12.500 1.1586 0.03674 0.03220 0.0195 0.0015 1.0000
12.750 1.1581 0.03977 0.03532 0.0188 0.0015 1.0000
13.000 1.1590 0.04263 0.03828 0.0180 0.0015 1.0000
13.250 1.1576 0.04581 0.04155 0.0171 0.0015 1.0000
13.500 1.1551 0.04912 0.04496 0.0162 0.0015 1.0000
13.750 1.1513 0.05264 0.04858 0.0152 0.0015 1.0000
14.000 1.1476 0.05618 0.05221 0.0142 0.0015 1.0000
14.250 1.1434 0.05985 0.05598 0.0130 0.0015 1.0000
14.500 1.1372 0.06383 0.06005 0.0117 0.0015 1.0000
14.750 1.1319 0.06791 0.06423 0.0103 0.0015 1.0000
15.000 1.1267 0.07205 0.06849 0.0087 0.0015 1.0000
15.250 1.1196 0.07657 0.07311 0.0070 0.0015 1.0000
15.500 1.1111 0.08142 0.07807 0.0052 0.0015 1.0000
15.750 1.1042 0.08612 0.08286 0.0033 0.0015 1.0000
16.000 1.0960 0.09112 0.08797 0.0012 0.0015 1.0000
16.250 1.0885 0.09614 0.09308 -0.0009 0.0015 1.0000
16.500 1.0785 0.10163 0.09867 -0.0032 0.0015 1.0000
16.750 1.0687 0.10725 0.10439 -0.0056 0.0015 1.0000
17.000 1.0593 0.11294 0.11017 -0.0082 0.0015 1.0000
17.250 1.0490 0.11887 0.11620 -0.0109 0.0015 1.0000
17.500 1.0378 0.12520 0.12263 -0.0139 0.0015 1.0000
17.750 1.0275 0.13154 0.12906 -0.0170 0.0015 1.0000
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Polar data table (+)
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