EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 100,000 Max Cl/Cd: 48.02 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2510-il-100000-n5.txt Download as CSV file: xf-eh2510-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4968 0.10052 0.09582 -0.0033 1.0000 0.0287
-9.250 -0.4945 0.09654 0.09188 -0.0046 1.0000 0.0282
-9.000 -0.4952 0.09209 0.08749 -0.0068 1.0000 0.0280
-8.750 -0.4970 0.08760 0.08305 -0.0095 1.0000 0.0279
-8.500 -0.5025 0.08262 0.07814 -0.0134 1.0000 0.0281
-8.250 -0.5088 0.07827 0.07383 -0.0159 1.0000 0.0278
-8.000 -0.5175 0.07362 0.06917 -0.0179 1.0000 0.0282
-7.750 -0.5213 0.06877 0.06424 -0.0197 1.0000 0.0286
-7.500 -0.5216 0.06391 0.05923 -0.0208 1.0000 0.0293
-7.000 -0.5155 0.05492 0.04985 -0.0206 1.0000 0.0295
-6.750 -0.5101 0.05065 0.04540 -0.0198 1.0000 0.0292
-6.500 -0.5026 0.04653 0.04103 -0.0188 1.0000 0.0290
-6.250 -0.4932 0.04261 0.03681 -0.0176 1.0000 0.0288
-6.000 -0.4821 0.03890 0.03275 -0.0161 1.0000 0.0288
-5.750 -0.4692 0.03548 0.02894 -0.0144 1.0000 0.0288
-5.500 -0.4547 0.03248 0.02553 -0.0126 1.0000 0.0290
-5.250 -0.4358 0.02975 0.02235 -0.0114 0.9942 0.0293
-5.000 -0.4006 0.02671 0.01876 -0.0132 0.9580 0.0300
-4.750 -0.3639 0.02418 0.01587 -0.0153 0.9260 0.0313
-4.500 -0.3279 0.02319 0.01469 -0.0171 0.8942 0.0352
-4.250 -0.2962 0.02197 0.01313 -0.0175 0.8641 0.0385
-4.000 -0.2679 0.02064 0.01148 -0.0170 0.8368 0.0399
-3.750 -0.2419 0.01959 0.01015 -0.0161 0.8117 0.0414
-3.500 -0.2181 0.01855 0.00901 -0.0150 0.7890 0.0439
-3.000 -0.1708 0.01719 0.00737 -0.0126 0.7497 0.0561
-2.750 -0.1473 0.01660 0.00674 -0.0115 0.7320 0.0719
-2.500 -0.1232 0.01620 0.00639 -0.0107 0.7155 0.1019
-2.250 -0.0995 0.01579 0.00610 -0.0099 0.7000 0.1465
-2.000 -0.0759 0.01530 0.00567 -0.0090 0.6856 0.1901
-1.750 -0.0549 0.01437 0.00527 -0.0079 0.6720 0.3290
-1.500 -0.0250 0.01304 0.00572 -0.0060 0.6590 0.8478
-1.250 0.0163 0.01335 0.00582 -0.0073 0.6452 0.9075
0.750 0.3298 0.01387 0.00457 -0.0248 0.5183 1.0000
1.000 0.3521 0.01391 0.00451 -0.0239 0.5099 1.0000
1.250 0.3745 0.01396 0.00450 -0.0230 0.5004 1.0000
1.500 0.3967 0.01403 0.00449 -0.0221 0.4894 1.0000
1.750 0.4188 0.01410 0.00449 -0.0211 0.4776 1.0000
2.000 0.4407 0.01419 0.00450 -0.0202 0.4654 1.0000
2.250 0.4629 0.01429 0.00453 -0.0192 0.4550 1.0000
2.500 0.4854 0.01440 0.00462 -0.0183 0.4453 1.0000
2.750 0.5078 0.01454 0.00472 -0.0174 0.4377 1.0000
3.000 0.5304 0.01468 0.00486 -0.0166 0.4304 1.0000
3.250 0.5529 0.01484 0.00505 -0.0157 0.4236 1.0000
3.500 0.5756 0.01501 0.00524 -0.0149 0.4164 1.0000
3.750 0.5982 0.01519 0.00542 -0.0140 0.4098 1.0000
4.000 0.6211 0.01539 0.00565 -0.0132 0.4028 1.0000
4.250 0.6437 0.01560 0.00587 -0.0123 0.3964 1.0000
4.500 0.6667 0.01581 0.00615 -0.0115 0.3891 1.0000
4.750 0.6894 0.01605 0.00646 -0.0107 0.3830 1.0000
5.000 0.7124 0.01629 0.00679 -0.0099 0.3756 1.0000
5.500 0.7580 0.01681 0.00744 -0.0083 0.3605 1.0000
5.750 0.7804 0.01706 0.00774 -0.0074 0.3498 1.0000
6.000 0.8025 0.01732 0.00805 -0.0065 0.3380 1.0000
6.250 0.8247 0.01761 0.00845 -0.0056 0.3273 1.0000
6.500 0.8473 0.01792 0.00890 -0.0049 0.3182 1.0000
6.750 0.8690 0.01823 0.00929 -0.0040 0.3046 1.0000
7.000 0.8900 0.01858 0.00967 -0.0030 0.2867 1.0000
7.250 0.9109 0.01897 0.01011 -0.0021 0.2677 1.0000
7.500 0.9306 0.01947 0.01058 -0.0011 0.2420 1.0000
7.750 0.9509 0.01999 0.01116 -0.0002 0.2220 1.0000
8.000 0.9690 0.02069 0.01182 0.0009 0.1918 1.0000
8.250 0.9849 0.02163 0.01272 0.0022 0.1552 1.0000
8.500 0.9934 0.02331 0.01402 0.0039 0.0940 1.0000
8.750 0.9935 0.02575 0.01597 0.0062 0.0376 1.0000
9.000 1.0045 0.02703 0.01732 0.0079 0.0313 1.0000
9.250 1.0158 0.02821 0.01865 0.0094 0.0288 1.0000
9.500 1.0245 0.02952 0.02011 0.0112 0.0270 1.0000
9.750 1.0295 0.03101 0.02174 0.0131 0.0255 1.0000
10.000 1.0272 0.03275 0.02360 0.0156 0.0240 1.0000
10.250 1.0228 0.03476 0.02574 0.0175 0.0231 1.0000
10.500 1.0204 0.03699 0.02814 0.0183 0.0220 1.0000
10.750 1.0168 0.03968 0.03099 0.0184 0.0206 1.0000
11.000 1.0119 0.04281 0.03427 0.0180 0.0198 1.0000
11.250 1.0060 0.04627 0.03787 0.0173 0.0192 1.0000
11.500 0.9991 0.05002 0.04177 0.0162 0.0187 1.0000
11.750 0.9907 0.05410 0.04596 0.0150 0.0181 1.0000
12.000 0.9840 0.05805 0.05003 0.0138 0.0179 1.0000
12.250 0.9750 0.06233 0.05441 0.0124 0.0174 1.0000
12.500 0.9685 0.06629 0.05845 0.0113 0.0170 1.0000
12.750 0.9656 0.06981 0.06219 0.0106 0.0164 1.0000
13.000 0.9647 0.07300 0.06549 0.0099 0.0162 1.0000
13.250 0.9651 0.07599 0.06859 0.0095 0.0156 1.0000
13.500 0.9671 0.07884 0.07155 0.0092 0.0152 1.0000
13.750 0.9681 0.08200 0.07480 0.0085 0.0145 1.0000
14.000 0.9694 0.08516 0.07803 0.0078 0.0140 1.0000
14.250 0.9692 0.08863 0.08153 0.0067 0.0134 1.0000
14.500 0.9683 0.09237 0.08538 0.0056 0.0127 1.0000
14.750 0.9692 0.09596 0.08913 0.0046 0.0124 1.0000
15.000 0.9669 0.10032 0.09366 0.0028 0.0120 1.0000
15.250 0.9632 0.10504 0.09852 0.0007 0.0115 1.0000
15.500 0.9596 0.10978 0.10340 -0.0014 0.0112 1.0000
15.750 0.9555 0.11480 0.10856 -0.0037 0.0111 1.0000
16.000 0.9500 0.12030 0.11423 -0.0064 0.0111 1.0000
16.250 0.9423 0.12650 0.12060 -0.0097 0.0111 1.0000
16.500 0.9328 0.13335 0.12761 -0.0134 0.0111 1.0000
16.750 0.9215 0.14098 0.13540 -0.0177 0.0111 1.0000
17.000 0.9073 0.14988 0.14447 -0.0227 0.0113 1.0000
17.250 0.8919 0.15975 0.15447 -0.0282 0.0118 1.0000
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Polar data table (+)
Polar graphs
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