EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.65 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh0009-il-1000000.txt Download as CSV file: xf-eh0009-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EH 0.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7961 0.08105 0.07938 -0.0025 1.0000 0.0039
-11.750 -0.8353 0.06628 0.06448 -0.0127 1.0000 0.0037
-11.500 -0.8551 0.05728 0.05535 -0.0202 1.0000 0.0037
-11.250 -0.8754 0.05023 0.04814 -0.0258 1.0000 0.0036
-11.000 -0.8976 0.04479 0.04251 -0.0284 1.0000 0.0037
-10.750 -0.9222 0.04054 0.03807 -0.0279 1.0000 0.0036
-10.500 -0.9444 0.03732 0.03464 -0.0244 1.0000 0.0036
-10.250 -0.9585 0.03375 0.03078 -0.0211 1.0000 0.0035
-10.000 -0.9633 0.03017 0.02685 -0.0184 1.0000 0.0035
-9.750 -0.9615 0.02690 0.02323 -0.0160 1.0000 0.0035
-9.500 -0.9528 0.02429 0.02031 -0.0140 1.0000 0.0035
-9.250 -0.9404 0.02205 0.01781 -0.0123 1.0000 0.0035
-9.000 -0.9237 0.02044 0.01599 -0.0109 1.0000 0.0037
-8.750 -0.9052 0.01911 0.01448 -0.0097 1.0000 0.0037
-8.500 -0.8853 0.01800 0.01320 -0.0086 1.0000 0.0038
-8.250 -0.8750 0.01522 0.01009 -0.0061 1.0000 0.0045
-8.000 -0.8528 0.01457 0.00938 -0.0053 1.0000 0.0049
-7.750 -0.8296 0.01406 0.00884 -0.0046 1.0000 0.0055
-7.500 -0.8069 0.01350 0.00821 -0.0038 1.0000 0.0060
-7.250 -0.7838 0.01300 0.00765 -0.0029 1.0000 0.0065
-7.000 -0.7599 0.01268 0.00729 -0.0023 1.0000 0.0068
-6.750 -0.7422 0.01144 0.00589 -0.0005 1.0000 0.0085
-6.500 -0.7190 0.01110 0.00554 0.0004 1.0000 0.0096
-6.250 -0.6957 0.01080 0.00520 0.0012 1.0000 0.0108
-6.000 -0.6719 0.01062 0.00501 0.0019 1.0000 0.0115
-5.750 -0.6519 0.00986 0.00416 0.0035 1.0000 0.0152
-5.500 -0.6294 0.00957 0.00386 0.0045 1.0000 0.0185
-5.250 -0.6081 0.00916 0.00343 0.0058 1.0000 0.0248
-5.000 -0.5862 0.00880 0.00312 0.0069 0.9999 0.0356
-4.750 -0.5516 0.00836 0.00279 0.0052 0.9975 0.0623
-4.500 -0.5164 0.00795 0.00253 0.0033 0.9949 0.0942
-4.250 -0.4827 0.00751 0.00229 0.0017 0.9918 0.1370
-4.000 -0.4493 0.00709 0.00207 0.0003 0.9879 0.1865
-3.750 -0.4142 0.00673 0.00188 -0.0015 0.9846 0.2311
-3.500 -0.3793 0.00635 0.00170 -0.0033 0.9811 0.2850
-3.250 -0.3488 0.00609 0.00156 -0.0040 0.9732 0.3232
-3.000 -0.3175 0.00579 0.00143 -0.0048 0.9654 0.3728
-2.750 -0.2879 0.00556 0.00132 -0.0052 0.9549 0.4122
-2.500 -0.2611 0.00536 0.00121 -0.0049 0.9412 0.4505
-2.250 -0.2353 0.00517 0.00113 -0.0044 0.9261 0.4909
-2.000 -0.2096 0.00504 0.00105 -0.0038 0.9099 0.5244
-1.500 -0.1578 0.00482 0.00093 -0.0027 0.8759 0.5880
-1.250 -0.1319 0.00474 0.00088 -0.0022 0.8576 0.6184
-1.000 -0.1056 0.00467 0.00084 -0.0017 0.8379 0.6473
-0.750 -0.0793 0.00462 0.00081 -0.0013 0.8178 0.6748
-0.500 -0.0529 0.00458 0.00079 -0.0009 0.7970 0.7018
0.000 0.0000 0.00454 0.00077 0.0000 0.7527 0.7528
0.500 0.0528 0.00458 0.00079 0.0009 0.7018 0.7969
0.750 0.0792 0.00462 0.00081 0.0013 0.6745 0.8178
1.000 0.1055 0.00467 0.00084 0.0018 0.6474 0.8379
1.250 0.1318 0.00474 0.00088 0.0022 0.6184 0.8576
1.500 0.1578 0.00482 0.00093 0.0027 0.5878 0.8758
1.750 0.1836 0.00493 0.00099 0.0033 0.5550 0.8934
2.000 0.2095 0.00504 0.00105 0.0038 0.5242 0.9100
2.250 0.2352 0.00517 0.00113 0.0044 0.4907 0.9261
2.500 0.2610 0.00536 0.00121 0.0049 0.4503 0.9413
2.750 0.2879 0.00556 0.00132 0.0052 0.4123 0.9550
3.000 0.3175 0.00579 0.00143 0.0048 0.3737 0.9655
3.250 0.3489 0.00609 0.00156 0.0039 0.3234 0.9733
3.500 0.3793 0.00635 0.00170 0.0033 0.2855 0.9813
3.750 0.4144 0.00673 0.00188 0.0015 0.2311 0.9846
4.000 0.4495 0.00708 0.00207 -0.0003 0.1873 0.9879
4.250 0.4829 0.00751 0.00228 -0.0018 0.1379 0.9919
4.500 0.5167 0.00795 0.00253 -0.0034 0.0946 0.9950
4.750 0.5519 0.00836 0.00279 -0.0052 0.0622 0.9977
5.000 0.5865 0.00880 0.00312 -0.0070 0.0355 1.0000
5.250 0.6077 0.00916 0.00343 -0.0057 0.0248 1.0000
5.500 0.6290 0.00957 0.00386 -0.0044 0.0185 1.0000
5.750 0.6514 0.00986 0.00415 -0.0034 0.0152 1.0000
6.000 0.6714 0.01062 0.00501 -0.0019 0.0115 1.0000
6.250 0.6952 0.01080 0.00520 -0.0011 0.0108 1.0000
6.500 0.7185 0.01112 0.00557 -0.0003 0.0097 1.0000
6.750 0.7418 0.01145 0.00590 0.0005 0.0085 1.0000
7.000 0.7596 0.01271 0.00733 0.0023 0.0068 1.0000
7.250 0.7836 0.01303 0.00768 0.0030 0.0065 1.0000
7.500 0.8070 0.01348 0.00818 0.0037 0.0060 1.0000
7.750 0.8298 0.01404 0.00881 0.0045 0.0054 1.0000
8.000 0.8524 0.01466 0.00950 0.0053 0.0050 1.0000
8.250 0.8751 0.01526 0.01013 0.0061 0.0046 1.0000
8.500 0.8846 0.01820 0.01342 0.0087 0.0038 1.0000
8.750 0.9052 0.01918 0.01456 0.0097 0.0037 1.0000
9.000 0.9245 0.02036 0.01590 0.0108 0.0036 1.0000
9.250 0.9406 0.02209 0.01785 0.0122 0.0036 1.0000
9.500 0.9533 0.02429 0.02031 0.0139 0.0035 1.0000
9.750 0.9617 0.02696 0.02330 0.0159 0.0035 1.0000
10.000 0.9637 0.03022 0.02691 0.0183 0.0035 1.0000
10.250 0.9602 0.03362 0.03063 0.0209 0.0035 1.0000
10.500 0.9436 0.03749 0.03482 0.0244 0.0036 1.0000
10.750 0.9236 0.04051 0.03803 0.0277 0.0036 1.0000
11.000 0.9012 0.04453 0.04225 0.0283 0.0036 1.0000
11.250 0.8792 0.04980 0.04769 0.0259 0.0037 1.0000
11.500 0.8586 0.05683 0.05488 0.0204 0.0037 1.0000
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Polar data table (+)
Polar graphs
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