HQ 0/7 AIRFOIL (hq07-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 0/7 AIRFOIL (hq07-il) Reynolds number: 1,000,000 Max Cl/Cd: 56.22 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq07-il-1000000-n5.txt Download as CSV file: xf-hq07-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/7 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6829 0.08366 0.08212 0.0053 1.0000 0.0033
-9.000 -0.6920 0.07712 0.07566 0.0006 1.0000 0.0032
-8.750 -0.7057 0.06971 0.06826 -0.0072 1.0000 0.0033
-8.500 -0.7215 0.06459 0.06308 -0.0096 1.0000 0.0033
-8.250 -0.7291 0.05881 0.05719 -0.0115 1.0000 0.0033
-8.000 -0.7341 0.05274 0.05096 -0.0125 1.0000 0.0032
-7.750 -0.7358 0.04648 0.04447 -0.0127 1.0000 0.0031
-7.500 -0.7338 0.04008 0.03777 -0.0121 1.0000 0.0030
-7.250 -0.7284 0.03343 0.03073 -0.0108 1.0000 0.0028
-7.000 -0.7208 0.02644 0.02319 -0.0088 1.0000 0.0026
-6.750 -0.7071 0.02118 0.01737 -0.0070 1.0000 0.0025
-6.500 -0.6885 0.01753 0.01325 -0.0055 1.0000 0.0023
-6.250 -0.6675 0.01485 0.01014 -0.0042 1.0000 0.0022
-6.000 -0.6449 0.01310 0.00813 -0.0031 1.0000 0.0021
-5.750 -0.6214 0.01186 0.00669 -0.0023 1.0000 0.0020
-5.500 -0.5972 0.01096 0.00564 -0.0016 1.0000 0.0020
-5.250 -0.5723 0.01028 0.00484 -0.0010 1.0000 0.0019
-5.000 -0.5470 0.00974 0.00419 -0.0005 1.0000 0.0019
-4.750 -0.5215 0.00929 0.00365 -0.0001 1.0000 0.0019
-4.500 -0.4958 0.00892 0.00321 0.0004 1.0000 0.0019
-4.250 -0.4645 0.00860 0.00282 -0.0005 0.9907 0.0019
-4.000 -0.4306 0.00833 0.00248 -0.0019 0.9762 0.0020
-3.750 -0.3962 0.00810 0.00214 -0.0033 0.9596 0.0024
-3.500 -0.3661 0.00792 0.00193 -0.0038 0.9352 0.0036
-3.250 -0.3407 0.00777 0.00174 -0.0032 0.9041 0.0096
-3.000 -0.3154 0.00767 0.00159 -0.0026 0.8778 0.0167
-2.750 -0.2903 0.00736 0.00140 -0.0021 0.8556 0.0581
-2.250 -0.2381 0.00695 0.00111 -0.0015 0.8175 0.1269
-2.000 -0.2117 0.00669 0.00094 -0.0014 0.8017 0.1819
-1.750 -0.1853 0.00643 0.00083 -0.0012 0.7864 0.2387
-1.500 -0.1604 0.00581 0.00068 -0.0010 0.7734 0.3797
-1.250 -0.1353 0.00525 0.00058 -0.0008 0.7622 0.5174
-1.000 -0.1091 0.00501 0.00054 -0.0005 0.7496 0.5923
-0.750 -0.0823 0.00491 0.00053 -0.0003 0.7349 0.6364
-0.500 -0.0549 0.00490 0.00051 -0.0002 0.7181 0.6529
-0.250 -0.0275 0.00491 0.00049 -0.0001 0.7002 0.6684
0.000 0.0001 0.00491 0.00049 0.0000 0.6839 0.6840
0.250 0.0276 0.00491 0.00049 0.0001 0.6684 0.7002
0.500 0.0550 0.00490 0.00051 0.0002 0.6529 0.7181
0.750 0.0824 0.00491 0.00053 0.0003 0.6364 0.7349
1.000 0.1093 0.00501 0.00054 0.0005 0.5927 0.7496
1.250 0.1354 0.00526 0.00058 0.0008 0.5153 0.7623
1.500 0.1604 0.00583 0.00068 0.0010 0.3760 0.7734
1.750 0.1854 0.00644 0.00083 0.0012 0.2352 0.7862
2.000 0.2119 0.00669 0.00094 0.0013 0.1813 0.8016
2.250 0.2382 0.00695 0.00111 0.0015 0.1259 0.8174
2.750 0.2905 0.00735 0.00140 0.0021 0.0589 0.8557
3.000 0.3155 0.00767 0.00160 0.0025 0.0160 0.8778
3.250 0.3409 0.00777 0.00175 0.0031 0.0096 0.9042
3.500 0.3664 0.00791 0.00193 0.0037 0.0038 0.9351
3.750 0.3964 0.00810 0.00214 0.0033 0.0024 0.9593
4.000 0.4306 0.00833 0.00247 0.0018 0.0020 0.9760
4.250 0.4648 0.00861 0.00282 0.0004 0.0019 0.9906
4.500 0.4956 0.00892 0.00321 -0.0003 0.0019 1.0000
4.750 0.5214 0.00930 0.00366 0.0001 0.0019 1.0000
5.000 0.5470 0.00973 0.00418 0.0005 0.0019 1.0000
5.250 0.5724 0.01028 0.00484 0.0010 0.0019 1.0000
5.500 0.5974 0.01096 0.00564 0.0015 0.0020 1.0000
5.750 0.6217 0.01187 0.00670 0.0022 0.0020 1.0000
6.000 0.6452 0.01314 0.00817 0.0031 0.0021 1.0000
6.250 0.6678 0.01494 0.01023 0.0041 0.0022 1.0000
6.500 0.6891 0.01751 0.01323 0.0053 0.0023 1.0000
6.750 0.7077 0.02123 0.01742 0.0068 0.0025 1.0000
7.000 0.7207 0.02687 0.02366 0.0088 0.0027 1.0000
7.250 0.7291 0.03353 0.03084 0.0106 0.0028 1.0000
7.500 0.7337 0.04046 0.03817 0.0119 0.0030 1.0000
7.750 0.7370 0.04648 0.04447 0.0125 0.0031 1.0000
8.000 0.7356 0.05269 0.05091 0.0123 0.0032 1.0000
8.250 0.7299 0.05895 0.05733 0.0112 0.0033 1.0000
8.500 0.7213 0.06491 0.06341 0.0092 0.0033 1.0000
8.750 0.7041 0.07027 0.06883 0.0064 0.0033 1.0000
9.000 0.6921 0.07751 0.07604 -0.0012 0.0032 1.0000
9.250 0.6845 0.08373 0.08220 -0.0056 0.0033 1.0000
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Polar data table (+)
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