EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 50,000 Max Cl/Cd: 32.28 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1590-il-50000-n5.txt Download as CSV file: xf-eh1590-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5600 0.09587 0.08925 -0.0020 1.0000 0.0461
-8.750 -0.5638 0.09059 0.08405 -0.0056 1.0000 0.0448
-8.500 -0.5721 0.08455 0.07808 -0.0108 1.0000 0.0434
-8.000 -0.5962 0.07282 0.06614 -0.0177 1.0000 0.0405
-7.750 -0.5963 0.06843 0.06167 -0.0183 1.0000 0.0402
-7.500 -0.5947 0.06412 0.05721 -0.0186 1.0000 0.0400
-7.250 -0.5915 0.05980 0.05269 -0.0187 1.0000 0.0398
-7.000 -0.5861 0.05552 0.04814 -0.0184 1.0000 0.0397
-6.750 -0.5783 0.05137 0.04365 -0.0179 1.0000 0.0397
-6.500 -0.5681 0.04733 0.03919 -0.0171 1.0000 0.0398
-6.250 -0.5551 0.04352 0.03490 -0.0160 1.0000 0.0401
-6.000 -0.5403 0.04003 0.03097 -0.0149 1.0000 0.0415
-5.750 -0.5227 0.03786 0.02870 -0.0142 1.0000 0.0447
-5.500 -0.5033 0.03537 0.02583 -0.0132 1.0000 0.0480
-5.250 -0.4816 0.03257 0.02251 -0.0120 1.0000 0.0503
-5.000 -0.4573 0.03000 0.01938 -0.0108 1.0000 0.0528
-4.750 -0.4347 0.02816 0.01746 -0.0101 1.0000 0.0585
-4.500 -0.4097 0.02646 0.01549 -0.0091 1.0000 0.0675
-4.250 -0.3845 0.02485 0.01379 -0.0082 1.0000 0.0763
-4.000 -0.3604 0.02359 0.01248 -0.0073 1.0000 0.0942
-3.750 -0.3368 0.02231 0.01122 -0.0064 1.0000 0.1149
-3.500 -0.3148 0.02117 0.01015 -0.0054 1.0000 0.1479
-3.250 -0.2957 0.01997 0.00921 -0.0042 1.0000 0.1958
-3.000 -0.2807 0.01863 0.00843 -0.0025 1.0000 0.2804
-2.750 -0.2749 0.01671 0.00813 0.0016 1.0000 0.5467
-2.500 -0.2209 0.01671 0.00871 0.0015 1.0000 0.8763
-2.250 -0.1111 0.01708 0.00826 -0.0117 1.0000 0.9696
-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 0.0090 0.01662 0.00709 -0.0179 0.9847 1.0000
-1.000 0.0576 0.01662 0.00689 -0.0228 0.9505 1.0000
-0.750 0.1041 0.01660 0.00668 -0.0269 0.9182 1.0000
-0.500 0.1450 0.01657 0.00646 -0.0296 0.8868 1.0000
-0.250 0.1774 0.01660 0.00632 -0.0305 0.8565 1.0000
0.000 0.2036 0.01668 0.00624 -0.0300 0.8281 1.0000
0.250 0.2268 0.01679 0.00621 -0.0289 0.8025 1.0000
0.500 0.2483 0.01694 0.00622 -0.0275 0.7781 1.0000
0.750 0.2695 0.01710 0.00626 -0.0261 0.7559 1.0000
1.000 0.2907 0.01728 0.00633 -0.0247 0.7351 1.0000
1.250 0.3120 0.01747 0.00643 -0.0233 0.7154 1.0000
1.500 0.3334 0.01769 0.00659 -0.0220 0.6962 1.0000
1.750 0.3551 0.01790 0.00673 -0.0206 0.6785 1.0000
2.000 0.3769 0.01814 0.00691 -0.0194 0.6611 1.0000
2.250 0.3989 0.01840 0.00715 -0.0182 0.6438 1.0000
2.500 0.4210 0.01867 0.00744 -0.0171 0.6271 1.0000
2.750 0.4433 0.01895 0.00771 -0.0159 0.6112 1.0000
3.000 0.4657 0.01924 0.00799 -0.0148 0.5956 1.0000
3.250 0.4882 0.01954 0.00831 -0.0137 0.5804 1.0000
3.500 0.5112 0.01987 0.00865 -0.0127 0.5653 1.0000
3.750 0.5341 0.02022 0.00913 -0.0118 0.5497 1.0000
4.000 0.5569 0.02059 0.00957 -0.0108 0.5344 1.0000
4.250 0.5796 0.02097 0.01004 -0.0099 0.5191 1.0000
4.500 0.6024 0.02137 0.01053 -0.0089 0.5039 1.0000
4.750 0.6252 0.02178 0.01105 -0.0079 0.4887 1.0000
5.000 0.6479 0.02220 0.01165 -0.0069 0.4734 1.0000
5.250 0.6707 0.02263 0.01221 -0.0059 0.4581 1.0000
5.500 0.6934 0.02306 0.01277 -0.0048 0.4426 1.0000
5.750 0.7161 0.02349 0.01334 -0.0037 0.4269 1.0000
6.000 0.7380 0.02401 0.01408 -0.0027 0.4092 1.0000
6.250 0.7599 0.02450 0.01483 -0.0016 0.3912 1.0000
6.500 0.7818 0.02493 0.01542 -0.0004 0.3728 1.0000
6.750 0.8025 0.02542 0.01616 0.0008 0.3509 1.0000
7.000 0.8221 0.02578 0.01670 0.0023 0.3249 1.0000
7.250 0.8376 0.02595 0.01694 0.0042 0.2825 1.0000
7.500 0.8493 0.02654 0.01734 0.0060 0.2174 1.0000
7.750 0.8577 0.02821 0.01859 0.0076 0.1412 1.0000
8.000 0.8608 0.03097 0.02083 0.0093 0.0893 1.0000
8.250 0.8658 0.03347 0.02318 0.0110 0.0680 1.0000
8.500 0.8711 0.03578 0.02561 0.0128 0.0595 1.0000
8.750 0.8762 0.03800 0.02788 0.0145 0.0529 1.0000
9.000 0.8824 0.04017 0.03021 0.0161 0.0474 1.0000
9.250 0.8882 0.04228 0.03244 0.0175 0.0431 1.0000
9.500 0.8922 0.04456 0.03475 0.0192 0.0406 1.0000
9.750 0.9035 0.04693 0.03732 0.0208 0.0389 1.0000
10.000 0.9156 0.04955 0.04027 0.0222 0.0373 1.0000
10.250 0.9233 0.05251 0.04355 0.0234 0.0361 1.0000
10.500 0.9250 0.05564 0.04697 0.0241 0.0351 1.0000
10.750 0.9221 0.05908 0.05068 0.0242 0.0341 1.0000
11.000 0.9158 0.06287 0.05470 0.0236 0.0333 1.0000
11.250 0.9073 0.06714 0.05919 0.0223 0.0329 1.0000
11.500 0.8962 0.07191 0.06417 0.0201 0.0325 1.0000
11.750 0.8819 0.07764 0.07010 0.0170 0.0326 1.0000
12.000 0.8649 0.08428 0.07692 0.0129 0.0328 1.0000
12.250 0.8421 0.09287 0.08572 0.0073 0.0343 1.0000
12.500 0.8213 0.10179 0.09476 0.0017 0.0354 1.0000
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Polar data table (+)
Polar graphs
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