Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 200,000 Max Cl/Cd: 52.41 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1070-il-200000.txt Download as CSV file: xf-eh1070-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Eh 1.0/7.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6039 0.11014 0.10671 0.0157 1.0000 0.0341
-9.250 -0.6037 0.10624 0.10286 0.0119 1.0000 0.0346
-7.750 -0.6193 0.07676 0.07346 -0.0093 1.0000 0.0360
-7.500 -0.6129 0.07313 0.06989 -0.0078 1.0000 0.0372
-7.250 -0.6067 0.06961 0.06635 -0.0082 1.0000 0.0384
-7.000 -0.6001 0.06567 0.06235 -0.0095 1.0000 0.0398
-6.750 -0.5922 0.06142 0.05799 -0.0111 1.0000 0.0417
-6.500 -0.5817 0.05698 0.05337 -0.0127 1.0000 0.0443
-6.250 -0.5655 0.05510 0.05076 -0.0136 1.0000 0.0477
-6.000 -0.5590 0.04731 0.04308 -0.0143 1.0000 0.0497
-5.750 -0.5430 0.04423 0.03998 -0.0141 1.0000 0.0519
-5.500 -0.5253 0.04118 0.03673 -0.0137 1.0000 0.0558
-5.250 -0.5084 0.03742 0.03247 -0.0132 1.0000 0.0628
-5.000 -0.4887 0.03468 0.02969 -0.0127 1.0000 0.0663
-4.750 -0.4691 0.03195 0.02650 -0.0118 1.0000 0.0763
-4.500 -0.4393 0.02341 0.01689 -0.0081 1.0000 0.0294
-4.250 -0.4143 0.02002 0.01284 -0.0063 1.0000 0.0266
-4.000 -0.3897 0.01858 0.01123 -0.0055 1.0000 0.0297
-3.750 -0.3644 0.01709 0.00951 -0.0045 1.0000 0.0319
-3.500 -0.3394 0.01544 0.00771 -0.0033 1.0000 0.0327
-3.250 -0.3155 0.01422 0.00640 -0.0021 1.0000 0.0345
-3.000 -0.2941 0.01278 0.00496 -0.0007 1.0000 0.0393
-2.750 -0.2718 0.01192 0.00415 0.0005 1.0000 0.0570
-2.500 -0.2544 0.01009 0.00323 0.0020 1.0000 0.2349
-2.250 -0.2492 0.00792 0.00304 0.0061 1.0000 0.6845
-2.000 -0.2328 0.00762 0.00332 0.0105 1.0000 0.8841
-1.750 -0.1780 0.00788 0.00343 0.0064 1.0000 0.9567
-1.500 -0.0993 0.00808 0.00331 -0.0033 1.0000 0.9831
-1.250 -0.0287 0.00799 0.00302 -0.0122 1.0000 0.9981
-1.000 -0.0034 0.00788 0.00286 -0.0122 1.0000 1.0000
-0.750 0.0123 0.00781 0.00277 -0.0105 1.0000 1.0000
-0.500 0.0222 0.00781 0.00277 -0.0077 1.0000 1.0000
-0.250 0.0659 0.00781 0.00271 -0.0115 0.9834 1.0000
0.000 0.1180 0.00777 0.00263 -0.0167 0.9563 1.0000
0.250 0.1633 0.00772 0.00251 -0.0202 0.9189 1.0000
0.500 0.1921 0.00771 0.00240 -0.0200 0.8763 1.0000
0.750 0.2127 0.00777 0.00232 -0.0181 0.8374 1.0000
1.000 0.2330 0.00787 0.00228 -0.0163 0.8029 1.0000
1.250 0.2541 0.00799 0.00227 -0.0146 0.7708 1.0000
1.500 0.2759 0.00813 0.00229 -0.0132 0.7412 1.0000
1.750 0.2983 0.00828 0.00232 -0.0120 0.7129 1.0000
2.000 0.3211 0.00844 0.00241 -0.0108 0.6856 1.0000
2.250 0.3443 0.00861 0.00250 -0.0098 0.6592 1.0000
2.500 0.3678 0.00879 0.00261 -0.0088 0.6341 1.0000
2.750 0.3916 0.00898 0.00274 -0.0079 0.6099 1.0000
3.000 0.4154 0.00918 0.00288 -0.0071 0.5857 1.0000
3.250 0.4393 0.00939 0.00309 -0.0062 0.5609 1.0000
3.500 0.4634 0.00959 0.00328 -0.0054 0.5350 1.0000
3.750 0.4875 0.00981 0.00349 -0.0046 0.5087 1.0000
4.000 0.5116 0.01004 0.00372 -0.0037 0.4808 1.0000
4.250 0.5349 0.01027 0.00388 -0.0028 0.4383 1.0000
4.500 0.5571 0.01063 0.00404 -0.0018 0.3602 1.0000
4.750 0.5788 0.01130 0.00435 -0.0009 0.2584 1.0000
5.000 0.5924 0.01416 0.00592 0.0006 0.0380 1.0000
5.250 0.6133 0.01556 0.00745 0.0018 0.0295 1.0000
5.500 0.6349 0.01682 0.00882 0.0030 0.0275 1.0000
5.750 0.6566 0.01829 0.01038 0.0043 0.0263 1.0000
6.000 0.6792 0.01990 0.01209 0.0055 0.0248 1.0000
6.250 0.7017 0.02119 0.01350 0.0063 0.0210 1.0000
6.500 0.7244 0.02338 0.01588 0.0074 0.0205 1.0000
6.750 0.7476 0.02589 0.01875 0.0087 0.0212 1.0000
7.000 0.7687 0.02982 0.02331 0.0105 0.0243 1.0000
7.250 0.7904 0.03401 0.02784 0.0121 0.0314 1.0000
13.500 0.7413 0.16406 0.16042 -0.0404 0.0328 1.0000
13.750 0.7484 0.16771 0.16408 -0.0415 0.0315 1.0000
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Polar data table (+)
Polar graphs
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