EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.4 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1090-il-1000000-n5.txt Download as CSV file: xf-eh1090-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8921 0.06725 0.06569 -0.0108 1.0000 0.0029
-12.000 -0.8784 0.06569 0.06413 -0.0119 1.0000 0.0029
-11.750 -0.9772 0.04185 0.03978 -0.0269 1.0000 0.0028
-11.500 -0.9981 0.03845 0.03619 -0.0241 1.0000 0.0027
-11.250 -0.9923 0.03711 0.03475 -0.0224 1.0000 0.0028
-11.000 -0.9939 0.03426 0.03168 -0.0205 1.0000 0.0028
-10.750 -1.0044 0.02977 0.02675 -0.0179 1.0000 0.0029
-10.500 -1.0047 0.02613 0.02271 -0.0155 1.0000 0.0031
-10.250 -0.9892 0.02465 0.02105 -0.0144 1.0000 0.0032
-10.000 -0.9710 0.02349 0.01976 -0.0135 1.0000 0.0033
-9.750 -0.9501 0.02272 0.01890 -0.0129 1.0000 0.0035
-9.500 -0.9302 0.02168 0.01773 -0.0121 1.0000 0.0036
-9.250 -0.9106 0.02051 0.01640 -0.0112 1.0000 0.0037
-9.000 -0.8892 0.01962 0.01539 -0.0104 1.0000 0.0038
-8.750 -0.8673 0.01877 0.01442 -0.0097 1.0000 0.0040
-8.500 -0.8461 0.01773 0.01323 -0.0088 1.0000 0.0041
-8.250 -0.8243 0.01675 0.01211 -0.0080 1.0000 0.0042
-8.000 -0.8016 0.01597 0.01122 -0.0073 1.0000 0.0044
-7.750 -0.7791 0.01513 0.01023 -0.0065 1.0000 0.0045
-7.500 -0.7561 0.01441 0.00941 -0.0057 1.0000 0.0046
-7.250 -0.7330 0.01373 0.00863 -0.0049 1.0000 0.0048
-7.000 -0.7097 0.01311 0.00793 -0.0042 1.0000 0.0049
-6.750 -0.6857 0.01271 0.00747 -0.0035 1.0000 0.0050
-6.500 -0.6594 0.01222 0.00693 -0.0033 0.9979 0.0051
-6.250 -0.6285 0.01149 0.00609 -0.0042 0.9893 0.0053
-6.000 -0.5972 0.01069 0.00516 -0.0051 0.9777 0.0059
-5.750 -0.5648 0.01023 0.00465 -0.0062 0.9606 0.0064
-5.500 -0.5353 0.00990 0.00424 -0.0066 0.9363 0.0069
-5.250 -0.5104 0.00966 0.00389 -0.0058 0.9069 0.0074
-5.000 -0.4860 0.00946 0.00358 -0.0050 0.8785 0.0079
-4.750 -0.4609 0.00929 0.00329 -0.0043 0.8517 0.0084
-4.500 -0.4354 0.00911 0.00296 -0.0037 0.8266 0.0092
-4.250 -0.4097 0.00892 0.00269 -0.0032 0.8021 0.0117
-4.000 -0.3835 0.00875 0.00245 -0.0028 0.7788 0.0160
-3.750 -0.3574 0.00856 0.00223 -0.0025 0.7565 0.0254
-3.500 -0.3311 0.00838 0.00203 -0.0022 0.7346 0.0379
-3.250 -0.3045 0.00824 0.00185 -0.0020 0.7141 0.0498
-3.000 -0.2778 0.00809 0.00170 -0.0017 0.6939 0.0665
-2.750 -0.2512 0.00792 0.00155 -0.0015 0.6751 0.0900
-2.250 -0.1981 0.00755 0.00129 -0.0011 0.6381 0.1537
-2.000 -0.1714 0.00739 0.00117 -0.0010 0.6211 0.1908
-1.750 -0.1449 0.00717 0.00107 -0.0008 0.6040 0.2388
-1.500 -0.1182 0.00700 0.00098 -0.0006 0.5880 0.2827
-1.250 -0.0918 0.00679 0.00090 -0.0005 0.5719 0.3413
-1.000 -0.0662 0.00645 0.00080 -0.0002 0.5562 0.4319
-0.750 -0.0403 0.00619 0.00074 0.0001 0.5409 0.5100
-0.500 -0.0140 0.00601 0.00070 0.0004 0.5256 0.5716
-0.250 0.0126 0.00589 0.00068 0.0006 0.5111 0.6184
0.000 0.0391 0.00578 0.00067 0.0008 0.4971 0.6673
0.250 0.0655 0.00567 0.00067 0.0012 0.4834 0.7171
0.500 0.0916 0.00558 0.00070 0.0016 0.4699 0.7645
0.750 0.1182 0.00555 0.00073 0.0020 0.4560 0.7966
1.000 0.1448 0.00555 0.00076 0.0023 0.4417 0.8251
1.250 0.1712 0.00556 0.00081 0.0027 0.4274 0.8508
1.500 0.1978 0.00559 0.00086 0.0031 0.4139 0.8734
1.750 0.2243 0.00564 0.00092 0.0035 0.4005 0.8917
2.000 0.2510 0.00570 0.00098 0.0039 0.3866 0.9064
2.250 0.2778 0.00580 0.00105 0.0042 0.3702 0.9182
2.500 0.3047 0.00591 0.00112 0.0044 0.3504 0.9282
2.750 0.3318 0.00605 0.00120 0.0046 0.3305 0.9371
3.000 0.3595 0.00615 0.00129 0.0047 0.3176 0.9459
3.250 0.3872 0.00628 0.00138 0.0047 0.3035 0.9550
3.500 0.4169 0.00640 0.00148 0.0043 0.2903 0.9614
3.750 0.4455 0.00655 0.00159 0.0041 0.2762 0.9684
4.000 0.4764 0.00674 0.00173 0.0034 0.2548 0.9728
4.250 0.5067 0.00697 0.00188 0.0027 0.2293 0.9775
4.500 0.5351 0.00729 0.00206 0.0024 0.1953 0.9827
4.750 0.5658 0.00788 0.00234 0.0013 0.1323 0.9855
5.000 0.5967 0.00832 0.00263 0.0002 0.0954 0.9883
5.250 0.6272 0.00869 0.00290 -0.0006 0.0708 0.9912
5.500 0.6565 0.00919 0.00325 -0.0013 0.0402 0.9941
5.750 0.6878 0.00964 0.00361 -0.0024 0.0207 0.9962
6.000 0.7189 0.01003 0.00395 -0.0033 0.0116 0.9985
6.250 0.7484 0.01035 0.00430 -0.0039 0.0093 1.0000
6.500 0.7709 0.01069 0.00465 -0.0029 0.0078 1.0000
6.750 0.7935 0.01106 0.00507 -0.0020 0.0070 1.0000
7.000 0.8167 0.01136 0.00541 -0.0012 0.0067 1.0000
7.250 0.8399 0.01169 0.00577 -0.0005 0.0061 1.0000
7.500 0.8631 0.01203 0.00614 0.0003 0.0055 1.0000
7.750 0.8860 0.01244 0.00660 0.0010 0.0051 1.0000
8.000 0.9084 0.01297 0.00718 0.0018 0.0045 1.0000
8.250 0.9302 0.01359 0.00789 0.0027 0.0041 1.0000
8.500 0.9533 0.01405 0.00841 0.0033 0.0040 1.0000
8.750 0.9760 0.01456 0.00898 0.0040 0.0038 1.0000
9.000 0.9985 0.01509 0.00958 0.0047 0.0036 1.0000
9.250 1.0203 0.01569 0.01025 0.0054 0.0034 1.0000
9.500 1.0420 0.01631 0.01094 0.0061 0.0032 1.0000
9.750 1.0632 0.01695 0.01167 0.0069 0.0030 1.0000
10.000 1.0844 0.01756 0.01234 0.0076 0.0028 1.0000
10.250 1.1046 0.01827 0.01312 0.0084 0.0027 1.0000
10.500 1.1237 0.01906 0.01398 0.0094 0.0025 1.0000
10.750 1.1385 0.02027 0.01532 0.0108 0.0023 1.0000
11.000 1.1510 0.02162 0.01682 0.0124 0.0022 1.0000
11.250 1.1585 0.02334 0.01872 0.0145 0.0021 1.0000
11.500 1.1732 0.02423 0.01971 0.0158 0.0021 1.0000
11.750 1.1829 0.02544 0.02104 0.0176 0.0021 1.0000
12.000 1.1867 0.02663 0.02235 0.0202 0.0020 1.0000
12.250 1.1861 0.02810 0.02395 0.0230 0.0020 1.0000
12.500 1.1901 0.02943 0.02540 0.0246 0.0020 1.0000
12.750 1.1850 0.03171 0.02783 0.0260 0.0020 1.0000
13.000 1.1787 0.03453 0.03081 0.0265 0.0019 1.0000
13.250 1.1813 0.03674 0.03312 0.0262 0.0019 1.0000
13.500 1.1763 0.04011 0.03663 0.0253 0.0019 1.0000
13.750 1.1537 0.04621 0.04297 0.0228 0.0019 1.0000
14.000 1.1603 0.04866 0.04547 0.0214 0.0018 1.0000
14.250 1.1466 0.05419 0.05116 0.0185 0.0019 1.0000
14.500 1.1297 0.06054 0.05766 0.0149 0.0018 1.0000
14.750 1.1169 0.06650 0.06374 0.0115 0.0019 1.0000
15.000 1.1004 0.07329 0.07067 0.0076 0.0019 1.0000
15.250 1.0712 0.08269 0.08023 0.0023 0.0019 1.0000
15.500 1.0566 0.08984 0.08748 -0.0018 0.0019 1.0000
15.750 1.0451 0.09666 0.09439 -0.0057 0.0019 1.0000
16.000 1.0201 0.10658 0.10443 -0.0112 0.0019 1.0000
16.250 0.9907 0.11804 0.11603 -0.0175 0.0019 1.0000
16.500 0.9600 0.13047 0.12856 -0.0242 0.0020 1.0000
16.750 0.9213 0.14591 0.14414 -0.0323 0.0021 1.0000
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Polar data table (+)
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