EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 50,000 Max Cl/Cd: 30.47 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1590-il-50000.txt Download as CSV file: xf-eh1590-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.5/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5424 0.10970 0.10321 0.0154 1.0000 0.2350
-8.750 -0.5611 0.10818 0.10184 0.0127 1.0000 0.2448
-8.500 -0.5523 0.10409 0.09778 0.0131 1.0000 0.2583
-8.250 -0.5481 0.10038 0.09412 0.0133 1.0000 0.2721
-8.000 -0.5493 0.09715 0.09097 0.0131 1.0000 0.2864
-7.750 -0.5234 0.09233 0.08607 0.0157 1.0000 0.3100
-7.500 -0.5390 0.09025 0.08413 0.0153 1.0000 0.3282
-7.250 -0.5091 0.08572 0.07956 0.0188 1.0000 0.3622
-7.000 -0.5000 0.08249 0.07637 0.0208 1.0000 0.3924
-6.750 -0.4934 0.07949 0.07343 0.0228 1.0000 0.4228
-5.750 -0.5296 0.04913 0.04160 -0.0156 1.0000 0.1315
-5.500 -0.5134 0.04500 0.03717 -0.0149 1.0000 0.1273
-5.250 -0.4959 0.04097 0.03225 -0.0138 1.0000 0.1193
-5.000 -0.4757 0.03735 0.02824 -0.0126 1.0000 0.1175
-4.750 -0.4541 0.03415 0.02453 -0.0113 1.0000 0.1174
-4.500 -0.4321 0.03144 0.02155 -0.0101 1.0000 0.1245
-4.250 -0.4088 0.02918 0.01881 -0.0087 1.0000 0.1346
-4.000 -0.3832 0.02679 0.01621 -0.0075 1.0000 0.1466
-3.750 -0.3594 0.02482 0.01430 -0.0065 1.0000 0.1729
-3.500 -0.3322 0.02270 0.01235 -0.0055 1.0000 0.2098
-3.250 -0.1207 0.01812 0.00989 -0.0261 1.0000 1.0000
-3.000 -0.1031 0.01771 0.00919 -0.0254 1.0000 1.0000
-2.750 -0.0854 0.01737 0.00857 -0.0246 1.0000 1.0000
-2.500 -0.0679 0.01709 0.00809 -0.0238 1.0000 1.0000
-2.250 -0.0510 0.01687 0.00771 -0.0227 1.0000 1.0000
-2.000 -0.0351 0.01670 0.00741 -0.0215 1.0000 1.0000
-1.750 -0.0213 0.01659 0.00722 -0.0200 1.0000 1.0000
-1.500 -0.0119 0.01658 0.00716 -0.0178 1.0000 1.0000
-1.250 -0.0106 0.01671 0.00724 -0.0145 1.0000 1.0000
-1.000 -0.0194 0.01704 0.00754 -0.0099 1.0000 1.0000
-0.750 -0.0305 0.01748 0.00792 -0.0054 1.0000 1.0000
-0.500 -0.0368 0.01796 0.00830 -0.0018 1.0000 1.0000
-0.250 -0.0384 0.01847 0.00870 0.0010 1.0000 1.0000
0.000 0.0303 0.01924 0.00933 -0.0088 0.9783 1.0000
0.250 0.1084 0.01985 0.00981 -0.0195 0.9548 1.0000
0.500 0.1812 0.02020 0.01013 -0.0288 0.9306 1.0000
0.750 0.2506 0.02036 0.01029 -0.0369 0.9070 1.0000
1.000 0.3071 0.02045 0.01039 -0.0421 0.8834 1.0000
1.250 0.3468 0.02066 0.01062 -0.0439 0.8594 1.0000
1.500 0.3745 0.02102 0.01098 -0.0436 0.8355 1.0000
1.750 0.4018 0.02137 0.01132 -0.0430 0.8140 1.0000
2.000 0.4235 0.02184 0.01178 -0.0415 0.7923 1.0000
2.250 0.4455 0.02228 0.01223 -0.0398 0.7727 1.0000
2.500 0.4646 0.02286 0.01287 -0.0381 0.7524 1.0000
2.750 0.4855 0.02333 0.01335 -0.0362 0.7342 1.0000
3.000 0.5045 0.02396 0.01401 -0.0344 0.7153 1.0000
3.250 0.5238 0.02460 0.01471 -0.0326 0.6968 1.0000
3.500 0.5441 0.02517 0.01531 -0.0307 0.6796 1.0000
3.750 0.5649 0.02570 0.01595 -0.0288 0.6631 1.0000
4.000 0.5830 0.02659 0.01694 -0.0273 0.6443 1.0000
4.250 0.6027 0.02732 0.01777 -0.0256 0.6268 1.0000
4.500 0.6234 0.02795 0.01848 -0.0238 0.6100 1.0000
4.750 0.6450 0.02852 0.01913 -0.0219 0.5937 1.0000
5.000 0.6629 0.02957 0.02042 -0.0206 0.5748 1.0000
5.250 0.6830 0.03037 0.02135 -0.0189 0.5568 1.0000
5.500 0.7049 0.03092 0.02203 -0.0170 0.5395 1.0000
5.750 0.7244 0.03182 0.02310 -0.0154 0.5206 1.0000
6.000 0.7443 0.03261 0.02408 -0.0136 0.5008 1.0000
6.250 0.7684 0.03280 0.02437 -0.0113 0.4817 1.0000
6.500 0.7865 0.03370 0.02558 -0.0095 0.4587 1.0000
6.750 0.8077 0.03400 0.02607 -0.0071 0.4344 1.0000
7.000 0.8312 0.03347 0.02565 -0.0041 0.4047 1.0000
7.250 0.8565 0.03054 0.02250 0.0005 0.3562 1.0000
7.500 0.8683 0.02850 0.02023 0.0051 0.2845 1.0000
7.750 0.8659 0.02981 0.02060 0.0097 0.1816 1.0000
8.000 0.8724 0.03253 0.02289 0.0123 0.1329 1.0000
8.250 0.8903 0.03537 0.02546 0.0141 0.1124 1.0000
8.500 0.9083 0.03802 0.02827 0.0155 0.0986 1.0000
8.750 0.9283 0.04089 0.03119 0.0166 0.0893 1.0000
9.000 0.9451 0.04459 0.03534 0.0179 0.0860 1.0000
9.250 0.9561 0.04841 0.03969 0.0193 0.0843 1.0000
9.500 0.9612 0.05256 0.04432 0.0207 0.0835 1.0000
9.750 0.9599 0.05687 0.04908 0.0219 0.0835 1.0000
10.000 0.9520 0.06130 0.05389 0.0229 0.0837 1.0000
10.250 0.9382 0.06580 0.05868 0.0234 0.0842 1.0000
10.500 0.9197 0.07010 0.06316 0.0238 0.0850 1.0000
10.750 0.8994 0.07495 0.06813 0.0228 0.0860 1.0000
11.000 0.8814 0.08048 0.07373 0.0205 0.0870 1.0000
11.250 0.8690 0.08637 0.07965 0.0179 0.0880 1.0000
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Polar data table (+)
Polar graphs
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