HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.0/9 AIRFOIL (hq109-il) Reynolds number: 50,000 Max Cl/Cd: 32.8 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq109-il-50000.txt Download as CSV file: xf-hq109-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/9 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5085 0.09612 0.08946 0.0049 1.0000 0.3272
-8.000 -0.4998 0.09256 0.08593 0.0060 1.0000 0.3487
-7.750 -0.5078 0.09061 0.08408 0.0068 1.0000 0.3713
-7.000 -0.5830 0.06164 0.05503 -0.0311 1.0000 0.1444
-6.750 -0.5853 0.05449 0.04713 -0.0342 1.0000 0.1219
-6.500 -0.5726 0.04954 0.04197 -0.0340 1.0000 0.1154
-6.250 -0.5613 0.04476 0.03637 -0.0336 1.0000 0.1082
-6.000 -0.5452 0.04089 0.03207 -0.0327 1.0000 0.1073
-5.750 -0.5285 0.03753 0.02817 -0.0315 1.0000 0.1108
-5.500 -0.5090 0.03468 0.02519 -0.0303 1.0000 0.1173
-5.250 -0.4871 0.03170 0.02161 -0.0289 1.0000 0.1212
-5.000 -0.4658 0.02931 0.01897 -0.0275 1.0000 0.1341
-4.750 -0.4430 0.02710 0.01648 -0.0261 1.0000 0.1504
-4.500 -0.4214 0.02513 0.01459 -0.0246 1.0000 0.1784
-4.250 -0.3990 0.02307 0.01276 -0.0229 1.0000 0.2117
-4.000 -0.3787 0.02095 0.01104 -0.0212 1.0000 0.2761
-3.750 -0.3729 0.01807 0.01019 -0.0166 1.0000 0.4990
-3.500 -0.3784 0.01829 0.01120 -0.0054 1.0000 0.7207
-3.250 -0.3765 0.01869 0.01158 0.0036 1.0000 0.8038
-3.000 -0.2027 0.02060 0.01207 -0.0111 1.0000 0.9502
-2.750 -0.0633 0.01924 0.00974 -0.0331 1.0000 1.0000
-2.500 -0.0545 0.01878 0.00920 -0.0317 1.0000 1.0000
-2.250 -0.0484 0.01840 0.00877 -0.0298 1.0000 1.0000
-2.000 -0.0460 0.01810 0.00844 -0.0273 1.0000 1.0000
-1.750 -0.0482 0.01786 0.00820 -0.0240 1.0000 1.0000
-1.500 -0.0561 0.01766 0.00799 -0.0198 1.0000 1.0000
-1.250 -0.0682 0.01747 0.00776 -0.0149 1.0000 1.0000
-1.000 -0.0789 0.01729 0.00752 -0.0102 1.0000 1.0000
-0.750 -0.0810 0.01719 0.00732 -0.0067 1.0000 1.0000
-0.500 -0.0725 0.01722 0.00720 -0.0048 1.0000 1.0000
-0.250 -0.0587 0.01735 0.00719 -0.0038 1.0000 1.0000
0.000 -0.0424 0.01754 0.00725 -0.0030 1.0000 1.0000
0.250 -0.0249 0.01779 0.00738 -0.0025 1.0000 1.0000
0.500 -0.0067 0.01809 0.00756 -0.0020 1.0000 1.0000
0.750 0.0118 0.01843 0.00782 -0.0017 1.0000 1.0000
1.000 0.0304 0.01882 0.00814 -0.0014 1.0000 1.0000
1.250 0.0490 0.01925 0.00852 -0.0012 1.0000 1.0000
1.500 0.0676 0.01972 0.00897 -0.0010 1.0000 1.0000
1.750 0.0860 0.02025 0.00948 -0.0009 1.0000 1.0000
2.000 0.1041 0.02083 0.01006 -0.0008 1.0000 1.0000
2.250 0.1220 0.02147 0.01071 -0.0008 1.0000 1.0000
2.500 0.1538 0.02245 0.01174 -0.0036 0.9938 1.0000
2.750 0.2256 0.02396 0.01347 -0.0134 0.9662 1.0000
3.000 0.2906 0.02509 0.01481 -0.0214 0.9400 1.0000
3.250 0.3515 0.02591 0.01589 -0.0280 0.9137 1.0000
3.500 0.4114 0.02643 0.01678 -0.0337 0.8859 1.0000
3.750 0.4682 0.02661 0.01733 -0.0380 0.8547 1.0000
4.000 0.5317 0.02619 0.01741 -0.0420 0.8201 1.0000
4.250 0.5830 0.02535 0.01697 -0.0424 0.7816 1.0000
4.500 0.6247 0.02411 0.01606 -0.0402 0.7378 1.0000
4.750 0.6556 0.02285 0.01506 -0.0359 0.6866 1.0000
5.000 0.6802 0.02179 0.01401 -0.0309 0.6241 1.0000
5.250 0.6992 0.02138 0.01340 -0.0261 0.5451 1.0000
5.500 0.7160 0.02183 0.01331 -0.0220 0.4564 1.0000
5.750 0.7308 0.02324 0.01413 -0.0187 0.3652 1.0000
6.000 0.7475 0.02529 0.01557 -0.0163 0.2866 1.0000
6.250 0.7672 0.02759 0.01753 -0.0145 0.2277 1.0000
6.500 0.7874 0.02967 0.01950 -0.0130 0.1850 1.0000
6.750 0.8107 0.03212 0.02189 -0.0118 0.1559 1.0000
7.000 0.8323 0.03478 0.02475 -0.0105 0.1343 1.0000
7.250 0.8538 0.03802 0.02829 -0.0092 0.1209 1.0000
7.500 0.8718 0.04112 0.03168 -0.0079 0.1090 1.0000
7.750 0.8880 0.04507 0.03614 -0.0064 0.1044 1.0000
8.000 0.9027 0.04916 0.04042 -0.0053 0.0991 1.0000
8.250 0.9067 0.05341 0.04536 -0.0035 0.0967 1.0000
8.500 0.9073 0.05802 0.05048 -0.0021 0.0955 1.0000
8.750 0.9040 0.06300 0.05587 -0.0011 0.0961 1.0000
9.000 0.8990 0.06813 0.06128 -0.0005 0.0977 1.0000
9.250 0.8967 0.07342 0.06670 -0.0001 0.0993 1.0000
9.500 0.8578 0.07880 0.07244 -0.0010 0.1039 1.0000
9.750 0.8266 0.08538 0.07906 -0.0039 0.1094 1.0000
10.000 0.8189 0.09131 0.08499 -0.0060 0.1120 1.0000
10.250 0.7839 0.10521 0.09881 -0.0176 0.1392 1.0000
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Polar data table (+)
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