dh4009sm (dh4009sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: dh4009sm (dh4009sm-il) Reynolds number: 500,000 Max Cl/Cd: 48.09 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dh4009sm-il-500000.txt Download as CSV file: xf-dh4009sm-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: dh4009sm
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6509 0.08431 0.08205 -0.0161 1.0000 0.0110
-9.000 -0.6642 0.07851 0.07622 -0.0206 1.0000 0.0109
-8.750 -0.6799 0.07432 0.07198 -0.0215 1.0000 0.0109
-8.500 -0.6902 0.07041 0.06801 -0.0210 1.0000 0.0110
-8.250 -0.6950 0.06647 0.06397 -0.0205 1.0000 0.0112
-8.000 -0.6965 0.06262 0.06000 -0.0197 1.0000 0.0115
-7.750 -0.6949 0.05886 0.05611 -0.0186 1.0000 0.0120
-7.500 -0.6898 0.05522 0.05230 -0.0173 1.0000 0.0128
-7.250 -0.6728 0.05288 0.04973 -0.0154 1.0000 0.0143
-7.000 -0.6577 0.05113 0.04775 -0.0136 1.0000 0.0148
-6.750 -0.6475 0.04841 0.04481 -0.0116 1.0000 0.0149
-6.500 -0.6367 0.04576 0.04193 -0.0096 1.0000 0.0150
-6.250 -0.6253 0.04303 0.03897 -0.0075 1.0000 0.0150
-6.000 -0.6277 0.03542 0.03099 -0.0044 1.0000 0.0158
-5.750 -0.6153 0.03237 0.02779 -0.0027 1.0000 0.0164
-5.500 -0.5999 0.03015 0.02545 -0.0011 1.0000 0.0169
-5.250 -0.5836 0.02819 0.02333 0.0006 1.0000 0.0176
-5.000 -0.5665 0.02640 0.02138 0.0023 1.0000 0.0185
-4.750 -0.5489 0.02476 0.01956 0.0042 1.0000 0.0197
-4.500 -0.5309 0.02339 0.01798 0.0063 1.0000 0.0212
-4.250 -0.5122 0.02326 0.01771 0.0085 1.0000 0.0235
-3.250 -0.3777 0.01438 0.00805 0.0048 0.9915 0.0205
-3.000 -0.3453 0.01291 0.00649 0.0040 0.9870 0.0192
-2.750 -0.3119 0.01214 0.00570 0.0027 0.9816 0.0211
-2.500 -0.2805 0.01106 0.00457 0.0018 0.9756 0.0198
-2.250 -0.2474 0.01023 0.00367 0.0006 0.9701 0.0192
-2.000 -0.2126 0.00960 0.00298 -0.0010 0.9654 0.0197
-1.750 -0.1779 0.00914 0.00243 -0.0026 0.9589 0.0220
-1.500 -0.1548 0.00614 0.00158 -0.0033 0.9536 0.6332
-1.250 -0.1240 0.00578 0.00171 -0.0037 0.9450 0.7681
-1.000 -0.0849 0.00578 0.00180 -0.0060 0.9394 0.8095
-0.750 -0.0482 0.00578 0.00177 -0.0080 0.9298 0.8223
-0.500 -0.0111 0.00577 0.00173 -0.0102 0.9201 0.8289
-0.250 0.0245 0.00578 0.00170 -0.0121 0.9096 0.8352
0.000 0.0567 0.00580 0.00169 -0.0131 0.8963 0.8418
0.250 0.0861 0.00583 0.00169 -0.0135 0.8818 0.8487
0.500 0.1148 0.00587 0.00171 -0.0136 0.8696 0.8555
0.750 0.1418 0.00590 0.00174 -0.0135 0.8581 0.8627
1.000 0.1684 0.00593 0.00179 -0.0132 0.8471 0.8700
1.250 0.1945 0.00596 0.00184 -0.0127 0.8323 0.8774
1.500 0.2188 0.00601 0.00185 -0.0117 0.8108 0.8854
1.750 0.2426 0.00605 0.00186 -0.0106 0.7847 0.8930
2.000 0.2644 0.00612 0.00186 -0.0091 0.7501 0.9022
2.250 0.2868 0.00622 0.00188 -0.0077 0.7069 0.9104
2.500 0.3078 0.00640 0.00193 -0.0060 0.6448 0.9196
2.750 0.3201 0.00713 0.00201 -0.0026 0.4720 0.9312
3.000 0.3261 0.00906 0.00252 0.0010 0.1121 0.9447
3.250 0.3518 0.00985 0.00305 0.0012 0.0401 0.9540
3.500 0.3825 0.01037 0.00361 0.0004 0.0303 0.9614
3.750 0.4137 0.01086 0.00414 -0.0005 0.0247 0.9689
4.000 0.4440 0.01199 0.00538 -0.0013 0.0215 0.9745
4.250 0.4770 0.01277 0.00624 -0.0026 0.0199 0.9794
4.500 0.5076 0.01393 0.00749 -0.0033 0.0191 0.9847
4.750 0.5406 0.01555 0.00923 -0.0044 0.0191 0.9879
5.000 0.5737 0.01720 0.01106 -0.0055 0.0189 0.9916
5.250 0.6064 0.01880 0.01285 -0.0066 0.0182 0.9952
5.500 0.6384 0.02180 0.01620 -0.0072 0.0191 0.9981
6.500 0.6714 0.03753 0.03313 0.0058 0.0220 1.0000
6.750 0.6802 0.04026 0.03612 0.0087 0.0220 1.0000
7.000 0.6886 0.04302 0.03913 0.0114 0.0219 1.0000
7.250 0.6970 0.04567 0.04203 0.0139 0.0218 1.0000
7.500 0.7214 0.04530 0.04198 0.0160 0.0193 1.0000
7.750 0.7300 0.04824 0.04514 0.0179 0.0175 1.0000
8.000 0.7351 0.05143 0.04850 0.0196 0.0167 1.0000
8.250 0.7380 0.05466 0.05189 0.0211 0.0160 1.0000
8.500 0.7387 0.05790 0.05526 0.0223 0.0156 1.0000
8.750 0.7370 0.06114 0.05862 0.0234 0.0152 1.0000
9.000 0.7316 0.06459 0.06218 0.0243 0.0150 1.0000
9.250 0.7202 0.06791 0.06557 0.0256 0.0148 1.0000
9.500 0.7041 0.07242 0.07018 0.0248 0.0149 1.0000
9.750 0.6866 0.07928 0.07713 0.0196 0.0150 1.0000
|
Polar data table (+)
Polar graphs
<< Back to dh4009sm (dh4009sm-il)