HQ 0/9 AIRFOIL (hq09-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 0/9 AIRFOIL (hq09-il) Reynolds number: 500,000 Max Cl/Cd: 51.83 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq09-il-500000.txt Download as CSV file: xf-hq09-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6093 0.08404 0.08204 0.0034 1.0000 0.0109
-9.750 -0.6255 0.07515 0.07318 -0.0009 1.0000 0.0104
-8.750 -0.8099 0.04371 0.04074 -0.0157 1.0000 0.0078
-8.500 -0.7987 0.04164 0.03850 -0.0148 1.0000 0.0076
-8.250 -0.8061 0.03538 0.03183 -0.0132 1.0000 0.0071
-8.000 -0.8044 0.02974 0.02562 -0.0112 1.0000 0.0069
-7.750 -0.7940 0.02540 0.02075 -0.0095 1.0000 0.0069
-7.500 -0.7772 0.02237 0.01729 -0.0081 1.0000 0.0071
-7.250 -0.7562 0.02047 0.01506 -0.0071 1.0000 0.0074
-7.000 -0.7400 0.01700 0.01118 -0.0054 1.0000 0.0085
-6.750 -0.7159 0.01635 0.01049 -0.0050 1.0000 0.0098
-6.500 -0.6919 0.01554 0.00957 -0.0044 1.0000 0.0114
-6.250 -0.6651 0.01552 0.00951 -0.0042 1.0000 0.0129
-6.000 -0.6439 0.01408 0.00800 -0.0033 1.0000 0.0182
-5.750 -0.6181 0.01375 0.00760 -0.0029 1.0000 0.0209
-5.500 -0.5962 0.01258 0.00631 -0.0020 1.0000 0.0234
-5.250 -0.5716 0.01213 0.00584 -0.0016 1.0000 0.0278
-5.000 -0.5471 0.01161 0.00526 -0.0010 1.0000 0.0304
-4.750 -0.5225 0.01116 0.00474 -0.0003 1.0000 0.0320
-4.500 -0.4999 0.01037 0.00389 0.0006 1.0000 0.0370
-4.250 -0.4757 0.00997 0.00347 0.0013 1.0000 0.0439
-4.000 -0.4533 0.00937 0.00300 0.0022 1.0000 0.0698
-3.750 -0.4323 0.00868 0.00262 0.0031 1.0000 0.1319
-3.500 -0.4123 0.00810 0.00236 0.0042 1.0000 0.2178
-3.250 -0.3807 0.00752 0.00211 0.0028 0.9953 0.2987
-3.000 -0.3462 0.00668 0.00187 0.0007 0.9870 0.4511
-2.750 -0.3103 0.00613 0.00177 -0.0014 0.9786 0.5676
-2.500 -0.2738 0.00590 0.00172 -0.0032 0.9685 0.6355
-2.250 -0.2396 0.00580 0.00167 -0.0045 0.9551 0.6705
-2.000 -0.2096 0.00573 0.00164 -0.0047 0.9385 0.6979
-1.750 -0.1827 0.00570 0.00161 -0.0042 0.9205 0.7219
-1.500 -0.1574 0.00567 0.00158 -0.0033 0.9034 0.7443
-1.250 -0.1315 0.00566 0.00154 -0.0026 0.8878 0.7584
-1.000 -0.1055 0.00567 0.00151 -0.0020 0.8731 0.7697
-0.750 -0.0790 0.00568 0.00149 -0.0015 0.8600 0.7814
-0.500 -0.0525 0.00568 0.00148 -0.0011 0.8476 0.7940
-0.250 -0.0261 0.00569 0.00147 -0.0006 0.8351 0.8069
0.000 0.0000 0.00569 0.00147 0.0000 0.8212 0.8212
0.250 0.0261 0.00569 0.00147 0.0006 0.8069 0.8351
0.500 0.0525 0.00568 0.00148 0.0011 0.7939 0.8476
0.750 0.0790 0.00568 0.00149 0.0015 0.7814 0.8600
1.000 0.1054 0.00567 0.00151 0.0020 0.7697 0.8731
1.250 0.1315 0.00566 0.00154 0.0026 0.7584 0.8878
1.500 0.1574 0.00567 0.00158 0.0033 0.7443 0.9034
1.750 0.1827 0.00570 0.00161 0.0042 0.7218 0.9205
2.000 0.2096 0.00573 0.00164 0.0047 0.6979 0.9384
2.250 0.2396 0.00580 0.00167 0.0045 0.6704 0.9552
2.500 0.2738 0.00590 0.00172 0.0032 0.6352 0.9686
2.750 0.3103 0.00613 0.00177 0.0014 0.5692 0.9788
3.000 0.3462 0.00668 0.00187 -0.0007 0.4510 0.9871
3.250 0.3808 0.00752 0.00211 -0.0028 0.2986 0.9955
3.500 0.4119 0.00809 0.00236 -0.0041 0.2183 1.0000
3.750 0.4319 0.00867 0.00261 -0.0031 0.1328 1.0000
4.000 0.4529 0.00937 0.00299 -0.0021 0.0704 1.0000
4.250 0.4754 0.00997 0.00347 -0.0012 0.0440 1.0000
4.500 0.4996 0.01036 0.00388 -0.0005 0.0371 1.0000
4.750 0.5224 0.01116 0.00474 0.0004 0.0321 1.0000
5.000 0.5470 0.01161 0.00525 0.0010 0.0304 1.0000
5.250 0.5715 0.01213 0.00584 0.0016 0.0278 1.0000
5.500 0.5962 0.01259 0.00632 0.0020 0.0235 1.0000
5.750 0.6183 0.01373 0.00758 0.0029 0.0208 1.0000
6.000 0.6440 0.01408 0.00800 0.0033 0.0182 1.0000
6.250 0.6647 0.01573 0.00973 0.0043 0.0130 1.0000
6.500 0.6920 0.01554 0.00958 0.0044 0.0113 1.0000
6.750 0.7161 0.01636 0.01049 0.0050 0.0098 1.0000
7.000 0.7402 0.01703 0.01122 0.0054 0.0086 1.0000
7.250 0.7559 0.02070 0.01532 0.0071 0.0074 1.0000
7.500 0.7773 0.02243 0.01736 0.0081 0.0071 1.0000
7.750 0.7942 0.02544 0.02079 0.0094 0.0069 1.0000
8.000 0.8049 0.02973 0.02561 0.0111 0.0069 1.0000
8.250 0.8060 0.03550 0.03195 0.0131 0.0071 1.0000
8.500 0.7996 0.04157 0.03842 0.0147 0.0076 1.0000
8.750 0.8108 0.04368 0.04071 0.0156 0.0078 1.0000
10.250 0.5984 0.09137 0.08935 -0.0067 0.0114 1.0000
10.500 0.5942 0.09570 0.09370 -0.0078 0.0134 1.0000
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Polar data table (+)
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