EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 500,000 Max Cl/Cd: 80.21 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1590-il-500000.txt Download as CSV file: xf-eh1590-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5631 0.10132 0.09913 0.0065 1.0000 0.0169
-9.500 -0.5636 0.09624 0.09409 0.0032 1.0000 0.0185
-6.000 -0.5571 0.02562 0.02130 -0.0106 1.0000 0.0176
-5.750 -0.5459 0.01841 0.01304 -0.0066 1.0000 0.0136
-5.500 -0.5244 0.01668 0.01107 -0.0053 1.0000 0.0136
-5.250 -0.5034 0.01505 0.00927 -0.0038 1.0000 0.0140
-5.000 -0.4823 0.01395 0.00807 -0.0025 1.0000 0.0147
-4.750 -0.4610 0.01318 0.00725 -0.0012 1.0000 0.0157
-4.500 -0.4350 0.01238 0.00637 -0.0008 0.9978 0.0166
-4.250 -0.3973 0.01159 0.00548 -0.0029 0.9888 0.0180
-4.000 -0.3588 0.01112 0.00496 -0.0052 0.9778 0.0199
-3.750 -0.3239 0.01004 0.00380 -0.0067 0.9610 0.0261
-3.500 -0.2901 0.00940 0.00319 -0.0077 0.9381 0.0469
-3.250 -0.2623 0.00908 0.00288 -0.0076 0.9085 0.0705
-3.000 -0.2381 0.00883 0.00265 -0.0066 0.8774 0.0987
-2.750 -0.2145 0.00856 0.00244 -0.0056 0.8478 0.1397
-2.500 -0.1910 0.00822 0.00223 -0.0047 0.8202 0.2027
-2.250 -0.1686 0.00766 0.00201 -0.0038 0.7948 0.3189
-2.000 -0.1510 0.00661 0.00176 -0.0022 0.7715 0.5604
-1.750 -0.1322 0.00604 0.00171 -0.0001 0.7495 0.7274
-1.500 -0.1092 0.00590 0.00171 0.0014 0.7287 0.8020
-1.250 -0.0845 0.00589 0.00170 0.0025 0.7088 0.8416
-1.000 -0.0596 0.00594 0.00170 0.0035 0.6902 0.8721
-0.750 -0.0341 0.00599 0.00169 0.0044 0.6720 0.8940
-0.500 -0.0086 0.00607 0.00169 0.0052 0.6545 0.9131
-0.250 0.0180 0.00616 0.00171 0.0059 0.6380 0.9283
0.000 0.0459 0.00629 0.00174 0.0063 0.6219 0.9428
0.250 0.0780 0.00645 0.00182 0.0058 0.6060 0.9572
0.500 0.1203 0.00670 0.00197 0.0032 0.5891 0.9697
0.750 0.1704 0.00688 0.00205 -0.0014 0.5717 0.9741
1.000 0.2063 0.00696 0.00204 -0.0031 0.5562 0.9778
1.250 0.2387 0.00705 0.00205 -0.0041 0.5416 0.9825
1.500 0.2765 0.00710 0.00202 -0.0064 0.5266 0.9846
1.750 0.3131 0.00717 0.00202 -0.0084 0.5118 0.9874
2.000 0.3484 0.00724 0.00203 -0.0101 0.4975 0.9908
2.250 0.3827 0.00732 0.00206 -0.0116 0.4837 0.9941
2.500 0.4190 0.00737 0.00206 -0.0136 0.4691 0.9967
2.750 0.4549 0.00742 0.00208 -0.0155 0.4550 0.9995
3.000 0.4809 0.00748 0.00211 -0.0153 0.4421 1.0000
3.250 0.5042 0.00754 0.00215 -0.0145 0.4297 1.0000
3.500 0.5275 0.00762 0.00223 -0.0137 0.4172 1.0000
3.750 0.5507 0.00771 0.00231 -0.0129 0.4048 1.0000
4.000 0.5739 0.00782 0.00240 -0.0121 0.3919 1.0000
4.250 0.5971 0.00794 0.00251 -0.0113 0.3790 1.0000
4.500 0.6203 0.00808 0.00264 -0.0104 0.3657 1.0000
4.750 0.6436 0.00822 0.00280 -0.0096 0.3516 1.0000
5.000 0.6669 0.00839 0.00295 -0.0088 0.3364 1.0000
5.250 0.6898 0.00860 0.00310 -0.0079 0.3125 1.0000
5.500 0.7122 0.00891 0.00328 -0.0071 0.2774 1.0000
5.750 0.7350 0.00920 0.00350 -0.0063 0.2509 1.0000
6.000 0.7574 0.00957 0.00379 -0.0054 0.2212 1.0000
6.250 0.7791 0.01006 0.00413 -0.0045 0.1813 1.0000
6.500 0.7978 0.01098 0.00469 -0.0033 0.1114 1.0000
6.750 0.8110 0.01271 0.00585 -0.0014 0.0240 1.0000
7.000 0.8318 0.01345 0.00669 -0.0002 0.0185 1.0000
7.250 0.8531 0.01410 0.00743 0.0009 0.0163 1.0000
7.500 0.8721 0.01506 0.00848 0.0021 0.0136 1.0000
7.750 0.8892 0.01627 0.00983 0.0037 0.0123 1.0000
8.000 0.9091 0.01709 0.01078 0.0048 0.0116 1.0000
8.250 0.9275 0.01810 0.01190 0.0061 0.0109 1.0000
8.500 0.9451 0.01920 0.01310 0.0075 0.0101 1.0000
8.750 0.9618 0.02042 0.01442 0.0089 0.0096 1.0000
9.000 0.9774 0.02183 0.01594 0.0104 0.0093 1.0000
9.250 0.9924 0.02336 0.01760 0.0119 0.0090 1.0000
9.500 1.0066 0.02519 0.01957 0.0135 0.0089 1.0000
9.750 1.0203 0.02708 0.02162 0.0150 0.0088 1.0000
10.000 1.0327 0.02911 0.02382 0.0166 0.0087 1.0000
10.250 1.0418 0.03140 0.02627 0.0180 0.0083 1.0000
10.500 1.0466 0.03436 0.02946 0.0198 0.0081 1.0000
10.750 1.0460 0.03753 0.03288 0.0220 0.0080 1.0000
11.000 1.0411 0.03996 0.03551 0.0247 0.0080 1.0000
11.250 1.0357 0.04221 0.03793 0.0268 0.0080 1.0000
11.500 1.0321 0.04428 0.04015 0.0279 0.0081 1.0000
11.750 1.0221 0.04752 0.04359 0.0282 0.0081 1.0000
12.000 1.0120 0.05106 0.04732 0.0275 0.0082 1.0000
12.250 0.9155 0.07105 0.06832 0.0198 0.0158 1.0000
12.500 0.8903 0.07913 0.07656 0.0142 0.0165 1.0000
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Polar data table (+)
Polar graphs
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