CHEN AIRFOIL (chen-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CHEN AIRFOIL (chen-il) Reynolds number: 500,000 Max Cl/Cd: 56.54 at α=12° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-chen-il-500000-n5.txt Download as CSV file: xf-chen-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CHEN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 0.0118 0.09620 0.09083 -0.0617 0.3239 0.0132
-8.750 0.0190 0.09364 0.08828 -0.0633 0.3238 0.0154
-8.500 0.0250 0.09104 0.08570 -0.0646 0.3237 0.0155
-8.000 0.0357 0.08598 0.08068 -0.0669 0.3237 0.0155
-7.750 0.0388 0.08336 0.07809 -0.0681 0.3237 0.0156
-7.250 0.0391 0.07839 0.07319 -0.0699 0.3235 0.0156
-7.000 0.0394 0.07632 0.07113 -0.0692 0.3234 0.0156
-6.750 0.0364 0.07444 0.06927 -0.0678 0.3233 0.0156
-6.250 0.0439 0.06999 0.06484 -0.0668 0.3233 0.0156
-5.750 0.0605 0.06650 0.06136 -0.0651 0.3232 0.0148
-5.500 0.0660 0.06423 0.05908 -0.0644 0.3231 0.0142
-5.250 0.0705 0.06144 0.05626 -0.0636 0.3230 0.0133
-5.000 0.0794 0.05928 0.05407 -0.0628 0.3229 0.0136
-4.750 0.0884 0.05689 0.05163 -0.0619 0.3228 0.0135
-4.500 0.0983 0.05447 0.04916 -0.0607 0.3229 0.0135
-4.250 0.1103 0.05234 0.04697 -0.0595 0.3227 0.0138
-4.000 0.1233 0.05029 0.04486 -0.0582 0.3227 0.0141
-3.750 0.1363 0.04804 0.04253 -0.0567 0.3226 0.0143
-3.500 0.1499 0.04579 0.04018 -0.0549 0.3225 0.0146
-3.250 0.1608 0.04241 0.03663 -0.0522 0.3224 0.0154
-3.000 0.1722 0.03941 0.03348 -0.0493 0.3224 0.0156
-2.750 0.1889 0.03797 0.03196 -0.0475 0.3223 0.0159
-2.500 0.2055 0.03633 0.03022 -0.0454 0.3222 0.0161
-2.000 0.2078 0.01944 0.01150 -0.0324 0.3221 0.0191
-1.750 0.2355 0.01874 0.01065 -0.0322 0.3220 0.0194
-1.500 0.2625 0.01838 0.01022 -0.0318 0.3219 0.0200
-1.250 0.2898 0.01812 0.00992 -0.0315 0.3217 0.0207
-1.000 0.3169 0.01792 0.00967 -0.0312 0.3217 0.0215
-0.750 0.3440 0.01776 0.00945 -0.0308 0.3216 0.0224
-0.250 0.3970 0.01750 0.00914 -0.0299 0.3213 0.0244
0.000 0.4227 0.01749 0.00912 -0.0293 0.3212 0.0264
0.250 0.4480 0.01746 0.00908 -0.0287 0.3211 0.0284
0.500 0.4729 0.01750 0.00914 -0.0279 0.3210 0.0310
0.750 0.4973 0.01754 0.00917 -0.0271 0.3209 0.0338
1.000 0.5216 0.01761 0.00926 -0.0262 0.3207 0.0374
1.250 0.5455 0.01771 0.00934 -0.0253 0.3207 0.0409
1.500 0.5695 0.01787 0.00953 -0.0244 0.3206 0.0452
1.750 0.5932 0.01798 0.00964 -0.0235 0.3204 0.0485
2.000 0.6170 0.01814 0.00983 -0.0226 0.3203 0.0518
2.250 0.6405 0.01833 0.01002 -0.0217 0.3202 0.0553
2.500 0.6639 0.01852 0.01025 -0.0207 0.3201 0.0591
2.750 0.6876 0.01875 0.01049 -0.0199 0.3200 0.0630
3.000 0.7110 0.01893 0.01066 -0.0189 0.3198 0.0662
3.250 0.7341 0.01907 0.01082 -0.0180 0.3195 0.0695
3.500 0.7575 0.01926 0.01102 -0.0171 0.3193 0.0730
3.750 0.7806 0.01949 0.01126 -0.0162 0.3191 0.0766
4.000 0.8033 0.01975 0.01153 -0.0152 0.3190 0.0798
4.250 0.8259 0.02000 0.01182 -0.0143 0.3188 0.0844
4.500 0.8484 0.02031 0.01215 -0.0133 0.3187 0.0881
4.750 0.8710 0.02063 0.01248 -0.0124 0.3185 0.0911
5.000 0.8929 0.02098 0.01287 -0.0114 0.3183 0.0955
5.250 0.9147 0.02139 0.01334 -0.0105 0.3181 0.1009
5.750 0.9561 0.02236 0.01442 -0.0083 0.3173 0.1138
6.000 0.9770 0.02263 0.01477 -0.0072 0.3172 0.1224
6.250 0.9973 0.02299 0.01520 -0.0060 0.3170 0.1352
6.500 1.0171 0.02332 0.01561 -0.0047 0.3167 0.1475
6.750 1.0365 0.02368 0.01605 -0.0034 0.3165 0.1571
7.250 1.0727 0.02449 0.01703 -0.0006 0.3155 0.1771
7.500 1.0900 0.02503 0.01766 0.0009 0.3151 0.1869
7.750 1.1060 0.02559 0.01834 0.0025 0.3146 0.2097
8.250 1.2714 0.02690 0.02137 -0.0239 0.3131 0.9846
8.750 1.3545 0.02857 0.02320 -0.0319 0.3115 0.9945
9.000 1.3894 0.02925 0.02394 -0.0345 0.3108 0.9975
9.250 1.4161 0.02997 0.02474 -0.0355 0.3103 0.9992
9.500 1.4380 0.03071 0.02555 -0.0355 0.3097 1.0000
9.750 1.4515 0.03127 0.02616 -0.0336 0.3092 1.0000
10.000 1.4766 0.03091 0.02579 -0.0330 0.3086 1.0000
10.250 1.4824 0.03202 0.02698 -0.0303 0.3082 1.0000
10.500 1.5067 0.03170 0.02666 -0.0296 0.3077 1.0000
10.750 1.5406 0.03068 0.02557 -0.0300 0.3071 1.0000
11.000 1.5843 0.02900 0.02377 -0.0317 0.3063 1.0000
11.250 1.5860 0.03041 0.02531 -0.0285 0.3063 1.0000
11.500 1.6224 0.02935 0.02417 -0.0293 0.3057 1.0000
11.750 1.6441 0.02933 0.02416 -0.0285 0.3053 1.0000
12.000 1.6584 0.02933 0.02422 -0.0265 0.3041 1.0000
12.500 1.0901 0.08704 0.08289 -0.0191 0.2606 1.0000
13.000 1.1197 0.08847 0.08434 -0.0184 0.2593 1.0000
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Polar data table (+)
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