HQ 0/9 AIRFOIL (hq09-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 0/9 AIRFOIL (hq09-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.9 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq09-il-1000000.txt Download as CSV file: xf-hq09-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.8237 0.05180 0.05008 -0.0198 1.0000 0.0045
-9.750 -0.8347 0.04981 0.04801 -0.0193 1.0000 0.0047
-9.500 -0.8462 0.04677 0.04483 -0.0177 1.0000 0.0047
-9.250 -0.8429 0.04488 0.04282 -0.0169 1.0000 0.0049
-9.000 -0.8783 0.03333 0.03060 -0.0134 1.0000 0.0038
-8.750 -0.8865 0.02638 0.02295 -0.0106 1.0000 0.0036
-8.500 -0.8780 0.02219 0.01824 -0.0087 1.0000 0.0035
-8.250 -0.8630 0.01923 0.01489 -0.0071 1.0000 0.0035
-8.000 -0.8444 0.01710 0.01245 -0.0059 1.0000 0.0035
-7.750 -0.8239 0.01549 0.01060 -0.0049 1.0000 0.0036
-7.500 -0.8020 0.01426 0.00918 -0.0040 1.0000 0.0037
-7.250 -0.7791 0.01328 0.00806 -0.0032 1.0000 0.0039
-7.000 -0.7551 0.01254 0.00719 -0.0026 1.0000 0.0042
-6.750 -0.7328 0.01146 0.00598 -0.0018 1.0000 0.0058
-6.500 -0.7072 0.01110 0.00560 -0.0014 1.0000 0.0070
-6.250 -0.6827 0.01050 0.00498 -0.0009 1.0000 0.0099
-6.000 -0.6561 0.01042 0.00493 -0.0008 1.0000 0.0123
-5.750 -0.6292 0.01040 0.00495 -0.0007 1.0000 0.0130
-5.500 -0.6056 0.00967 0.00413 0.0000 1.0000 0.0166
-5.250 -0.5798 0.00948 0.00394 0.0003 1.0000 0.0191
-5.000 -0.5543 0.00925 0.00369 0.0007 1.0000 0.0206
-4.750 -0.5287 0.00911 0.00355 0.0011 1.0000 0.0218
-4.500 -0.5052 0.00857 0.00294 0.0019 1.0000 0.0260
-4.250 -0.4802 0.00827 0.00265 0.0024 0.9996 0.0306
-4.000 -0.4447 0.00791 0.00233 0.0006 0.9922 0.0454
-3.750 -0.4086 0.00750 0.00206 -0.0014 0.9828 0.0794
-3.500 -0.3735 0.00695 0.00178 -0.0034 0.9698 0.1454
-3.250 -0.3418 0.00654 0.00160 -0.0045 0.9514 0.2139
-2.750 -0.2919 0.00587 0.00125 -0.0034 0.9015 0.3365
-2.500 -0.2683 0.00542 0.00109 -0.0027 0.8803 0.4413
-2.250 -0.2437 0.00507 0.00098 -0.0021 0.8638 0.5266
-2.000 -0.2180 0.00487 0.00093 -0.0017 0.8495 0.5889
-1.750 -0.1913 0.00479 0.00089 -0.0013 0.8363 0.6262
-1.500 -0.1644 0.00472 0.00085 -0.0011 0.8242 0.6560
-1.250 -0.1372 0.00468 0.00083 -0.0009 0.8134 0.6795
-1.000 -0.1102 0.00464 0.00082 -0.0006 0.8021 0.7034
-0.750 -0.0828 0.00463 0.00080 -0.0004 0.7891 0.7167
-0.500 -0.0552 0.00463 0.00077 -0.0003 0.7744 0.7271
-0.250 -0.0276 0.00464 0.00076 -0.0001 0.7613 0.7381
0.250 0.0277 0.00464 0.00076 0.0001 0.7381 0.7613
0.500 0.0553 0.00463 0.00077 0.0003 0.7271 0.7744
0.750 0.0828 0.00463 0.00080 0.0004 0.7167 0.7891
1.000 0.1102 0.00464 0.00082 0.0006 0.7034 0.8020
1.250 0.1372 0.00468 0.00083 0.0009 0.6795 0.8133
1.500 0.1644 0.00472 0.00085 0.0011 0.6560 0.8242
1.750 0.1913 0.00479 0.00089 0.0013 0.6260 0.8363
2.000 0.2180 0.00487 0.00093 0.0017 0.5894 0.8496
2.250 0.2437 0.00507 0.00098 0.0021 0.5254 0.8639
2.500 0.2683 0.00542 0.00109 0.0027 0.4412 0.8803
2.750 0.2918 0.00588 0.00126 0.0034 0.3333 0.9017
3.250 0.3418 0.00654 0.00160 0.0045 0.2139 0.9515
3.500 0.3735 0.00695 0.00178 0.0034 0.1454 0.9699
3.750 0.4087 0.00750 0.00206 0.0014 0.0793 0.9830
4.000 0.4448 0.00791 0.00233 -0.0006 0.0456 0.9922
4.250 0.4803 0.00827 0.00265 -0.0025 0.0307 0.9998
4.500 0.5049 0.00857 0.00293 -0.0019 0.0260 1.0000
4.750 0.5285 0.00911 0.00355 -0.0010 0.0218 1.0000
5.000 0.5540 0.00927 0.00371 -0.0007 0.0207 1.0000
5.250 0.5796 0.00948 0.00394 -0.0003 0.0191 1.0000
5.500 0.6055 0.00967 0.00413 0.0000 0.0166 1.0000
5.750 0.6291 0.01041 0.00495 0.0007 0.0130 1.0000
6.000 0.6561 0.01042 0.00493 0.0008 0.0123 1.0000
6.250 0.6827 0.01052 0.00501 0.0009 0.0100 1.0000
6.500 0.7073 0.01110 0.00560 0.0014 0.0070 1.0000
6.750 0.7329 0.01145 0.00598 0.0017 0.0058 1.0000
7.000 0.7564 0.01226 0.00685 0.0024 0.0044 1.0000
7.250 0.7791 0.01331 0.00809 0.0032 0.0039 1.0000
7.500 0.8021 0.01425 0.00918 0.0039 0.0037 1.0000
7.750 0.8240 0.01550 0.01061 0.0048 0.0036 1.0000
8.000 0.8446 0.01710 0.01245 0.0059 0.0035 1.0000
8.250 0.8631 0.01927 0.01492 0.0071 0.0035 1.0000
8.500 0.8782 0.02220 0.01825 0.0086 0.0035 1.0000
8.750 0.8865 0.02643 0.02301 0.0106 0.0036 1.0000
9.000 0.8775 0.03357 0.03085 0.0134 0.0038 1.0000
9.250 0.8498 0.04174 0.03955 0.0161 0.0042 1.0000
9.500 0.8522 0.04434 0.04231 0.0171 0.0043 1.0000
9.750 0.8481 0.04704 0.04515 0.0187 0.0044 1.0000
10.000 0.8253 0.05161 0.04989 0.0198 0.0045 1.0000
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Polar data table (+)
Polar graphs
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