HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/8 AIRFOIL (hq258-il) Reynolds number: 50,000 Max Cl/Cd: 39.21 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq258-il-50000.txt Download as CSV file: xf-hq258-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4118 0.09885 0.09228 -0.0191 1.0000 0.2174
-7.750 -0.4114 0.09602 0.08955 -0.0189 1.0000 0.2290
-7.500 -0.4324 0.09551 0.08922 -0.0196 1.0000 0.2374
-7.250 -0.4104 0.09054 0.08425 -0.0172 1.0000 0.2558
-7.000 -0.4088 0.08785 0.08165 -0.0156 1.0000 0.2729
-6.750 -0.4154 0.08587 0.07980 -0.0139 1.0000 0.2894
-6.500 -0.4287 0.08440 0.07849 -0.0133 1.0000 0.3052
-6.250 -0.4224 0.08139 0.07556 -0.0100 1.0000 0.3319
-6.000 -0.4208 0.07896 0.07323 -0.0069 1.0000 0.3591
-5.750 -0.4009 0.07532 0.06960 -0.0022 1.0000 0.3942
-5.500 -0.3932 0.07280 0.06716 0.0022 1.0000 0.4340
-4.250 -0.3781 0.04975 0.04380 -0.0330 1.0000 0.2692
-4.000 -0.3075 0.03960 0.03172 -0.0480 1.0000 0.1242
-3.750 -0.2785 0.03638 0.02771 -0.0487 1.0000 0.1144
-3.500 -0.2529 0.03354 0.02441 -0.0487 1.0000 0.1139
-3.250 -0.2263 0.03088 0.02133 -0.0484 1.0000 0.1113
-3.000 -0.1990 0.02857 0.01857 -0.0478 1.0000 0.1098
-2.750 -0.1718 0.02659 0.01608 -0.0469 1.0000 0.1124
-2.500 -0.1466 0.02487 0.01421 -0.0458 1.0000 0.1248
-2.250 -0.1225 0.02329 0.01261 -0.0445 1.0000 0.1486
-2.000 -0.0960 0.02149 0.01101 -0.0438 1.0000 0.2056
-1.750 -0.0855 0.01783 0.01039 -0.0381 1.0000 0.7607
-1.500 -0.0652 0.01717 0.00937 -0.0345 1.0000 1.0000
-1.250 -0.0410 0.01734 0.00898 -0.0346 1.0000 1.0000
-1.000 -0.0173 0.01756 0.00875 -0.0348 1.0000 1.0000
-0.750 0.0059 0.01781 0.00857 -0.0348 1.0000 1.0000
-0.500 0.0287 0.01811 0.00855 -0.0349 1.0000 1.0000
-0.250 0.0511 0.01844 0.00860 -0.0348 1.0000 1.0000
0.000 0.0732 0.01880 0.00873 -0.0348 1.0000 1.0000
0.250 0.0949 0.01921 0.00894 -0.0348 1.0000 1.0000
0.500 0.1162 0.01965 0.00915 -0.0347 1.0000 1.0000
0.750 0.1372 0.02013 0.00949 -0.0346 1.0000 1.0000
1.000 0.1578 0.02065 0.00989 -0.0346 1.0000 1.0000
1.250 0.1781 0.02122 0.01036 -0.0345 1.0000 1.0000
1.500 0.1979 0.02184 0.01090 -0.0345 1.0000 1.0000
1.750 0.2174 0.02250 0.01151 -0.0345 1.0000 1.0000
2.000 0.2364 0.02323 0.01219 -0.0345 1.0000 1.0000
2.250 0.2549 0.02401 0.01296 -0.0346 1.0000 1.0000
2.500 0.2730 0.02487 0.01381 -0.0347 1.0000 1.0000
2.750 0.3315 0.02651 0.01551 -0.0424 0.9791 1.0000
3.000 0.3929 0.02794 0.01710 -0.0500 0.9553 1.0000
3.250 0.4457 0.02895 0.01826 -0.0556 0.9304 1.0000
3.500 0.4975 0.02975 0.01925 -0.0605 0.9049 1.0000
3.750 0.5498 0.03029 0.02003 -0.0649 0.8783 1.0000
4.000 0.6054 0.03044 0.02058 -0.0690 0.8504 1.0000
4.250 0.6695 0.02991 0.02045 -0.0733 0.8214 1.0000
4.500 0.7197 0.02914 0.02007 -0.0746 0.7890 1.0000
4.750 0.7769 0.02744 0.01892 -0.0752 0.7555 1.0000
5.000 0.8218 0.02572 0.01757 -0.0735 0.7154 1.0000
5.250 0.8577 0.02429 0.01638 -0.0705 0.6656 1.0000
5.500 0.8890 0.02328 0.01539 -0.0669 0.6048 1.0000
5.750 0.9124 0.02327 0.01520 -0.0634 0.5351 1.0000
6.000 0.9332 0.02401 0.01575 -0.0604 0.4669 1.0000
6.250 0.9535 0.02526 0.01668 -0.0579 0.4051 1.0000
6.500 0.9726 0.02684 0.01805 -0.0557 0.3483 1.0000
6.750 0.9889 0.02854 0.01957 -0.0532 0.2911 1.0000
7.000 0.9971 0.03036 0.02105 -0.0499 0.2215 1.0000
7.250 0.9947 0.03250 0.02262 -0.0457 0.1420 1.0000
7.500 1.0081 0.03563 0.02520 -0.0436 0.0975 1.0000
7.750 1.0350 0.03931 0.02914 -0.0424 0.0818 1.0000
8.000 1.0568 0.04271 0.03257 -0.0415 0.0717 1.0000
8.250 1.0732 0.04615 0.03674 -0.0396 0.0667 1.0000
8.500 1.0878 0.05022 0.04130 -0.0379 0.0642 1.0000
8.750 1.0968 0.05468 0.04630 -0.0360 0.0638 1.0000
9.000 1.0984 0.05944 0.05162 -0.0339 0.0642 1.0000
9.250 1.0937 0.06435 0.05702 -0.0318 0.0651 1.0000
9.500 1.0841 0.06920 0.06227 -0.0300 0.0662 1.0000
9.750 1.0699 0.07397 0.06735 -0.0284 0.0672 1.0000
10.000 1.0516 0.07833 0.07191 -0.0269 0.0682 1.0000
10.250 1.0317 0.08297 0.07669 -0.0265 0.0690 1.0000
10.500 1.0127 0.08811 0.08194 -0.0274 0.0698 1.0000
10.750 0.9975 0.09373 0.08763 -0.0293 0.0707 1.0000
11.000 0.9910 0.09961 0.09353 -0.0308 0.0717 1.0000
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Polar data table (+)
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