HT08 (ht08-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 1,000,000 Max Cl/Cd: 56.72 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht08-il-1000000.txt Download as CSV file: xf-ht08-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HT08
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.8676 0.05232 0.05066 0.0018 1.0000 0.0075
-8.500 -0.8843 0.03424 0.03170 -0.0037 1.0000 0.0073
-8.250 -0.8824 0.02503 0.02155 -0.0042 1.0000 0.0074
-8.000 -0.8650 0.02107 0.01708 -0.0039 1.0000 0.0077
-7.750 -0.8421 0.01923 0.01500 -0.0037 1.0000 0.0080
-7.500 -0.8176 0.01796 0.01356 -0.0035 1.0000 0.0082
-7.250 -0.7925 0.01686 0.01230 -0.0032 1.0000 0.0086
-7.000 -0.7668 0.01591 0.01121 -0.0030 1.0000 0.0090
-6.750 -0.7406 0.01519 0.01037 -0.0028 1.0000 0.0096
-6.500 -0.7142 0.01441 0.00947 -0.0026 1.0000 0.0102
-6.250 -0.6874 0.01381 0.00876 -0.0024 1.0000 0.0106
-6.000 -0.6621 0.01210 0.00681 -0.0021 1.0000 0.0113
-5.750 -0.6356 0.01121 0.00584 -0.0019 1.0000 0.0123
-5.500 -0.6084 0.01074 0.00533 -0.0018 1.0000 0.0131
-5.250 -0.5810 0.01031 0.00484 -0.0017 1.0000 0.0142
-5.000 -0.5534 0.01003 0.00453 -0.0016 1.0000 0.0153
-4.750 -0.5261 0.00934 0.00374 -0.0015 1.0000 0.0170
-4.500 -0.4985 0.00890 0.00328 -0.0014 1.0000 0.0194
-4.250 -0.4706 0.00862 0.00297 -0.0013 1.0000 0.0215
-4.000 -0.4428 0.00829 0.00260 -0.0013 1.0000 0.0242
-3.750 -0.4149 0.00796 0.00229 -0.0012 1.0000 0.0302
-3.500 -0.3869 0.00767 0.00201 -0.0012 1.0000 0.0379
-3.250 -0.3589 0.00740 0.00178 -0.0011 1.0000 0.0505
-3.000 -0.3310 0.00713 0.00160 -0.0011 1.0000 0.0703
-2.750 -0.3031 0.00685 0.00144 -0.0012 1.0000 0.0983
-2.500 -0.2752 0.00657 0.00131 -0.0012 1.0000 0.1337
-2.250 -0.2473 0.00628 0.00118 -0.0012 1.0000 0.1782
-2.000 -0.2194 0.00598 0.00108 -0.0013 1.0000 0.2309
-1.750 -0.1915 0.00568 0.00099 -0.0014 1.0000 0.2911
-1.500 -0.1637 0.00536 0.00092 -0.0014 1.0000 0.3626
-1.250 -0.1361 0.00500 0.00086 -0.0015 1.0000 0.4466
-1.000 -0.1088 0.00459 0.00081 -0.0015 1.0000 0.5536
-0.750 -0.0820 0.00413 0.00079 -0.0013 1.0000 0.6765
-0.500 -0.0568 0.00367 0.00079 -0.0006 1.0000 0.8012
-0.250 -0.0361 0.00330 0.00082 0.0015 1.0000 0.9165
0.000 0.0001 0.00320 0.00082 0.0000 0.9953 0.9953
0.250 0.0362 0.00330 0.00082 -0.0015 0.9163 1.0000
0.500 0.0569 0.00368 0.00079 0.0006 0.8004 1.0000
0.750 0.0822 0.00413 0.00079 0.0013 0.6766 1.0000
1.000 0.1089 0.00459 0.00081 0.0015 0.5531 1.0000
1.250 0.1362 0.00500 0.00086 0.0015 0.4471 1.0000
1.500 0.1639 0.00536 0.00092 0.0014 0.3621 1.0000
1.750 0.1917 0.00568 0.00099 0.0014 0.2909 1.0000
2.000 0.2195 0.00599 0.00108 0.0013 0.2295 1.0000
2.250 0.2474 0.00628 0.00118 0.0012 0.1781 1.0000
2.500 0.2753 0.00657 0.00131 0.0012 0.1336 1.0000
2.750 0.3032 0.00685 0.00144 0.0011 0.0982 1.0000
3.000 0.3312 0.00714 0.00160 0.0011 0.0701 1.0000
3.250 0.3591 0.00740 0.00178 0.0011 0.0502 1.0000
3.500 0.3871 0.00767 0.00201 0.0011 0.0378 1.0000
3.750 0.4150 0.00796 0.00229 0.0012 0.0302 1.0000
4.000 0.4429 0.00829 0.00260 0.0012 0.0242 1.0000
4.250 0.4708 0.00862 0.00297 0.0013 0.0215 1.0000
4.500 0.4986 0.00890 0.00328 0.0014 0.0193 1.0000
4.750 0.5263 0.00935 0.00375 0.0015 0.0170 1.0000
5.000 0.5536 0.01004 0.00454 0.0016 0.0153 1.0000
5.250 0.5812 0.01032 0.00486 0.0017 0.0142 1.0000
5.500 0.6086 0.01075 0.00534 0.0018 0.0131 1.0000
5.750 0.6358 0.01121 0.00584 0.0019 0.0122 1.0000
6.000 0.6624 0.01207 0.00679 0.0021 0.0113 1.0000
6.250 0.6875 0.01383 0.00879 0.0024 0.0106 1.0000
6.500 0.7144 0.01443 0.00949 0.0026 0.0102 1.0000
6.750 0.7409 0.01517 0.01034 0.0028 0.0096 1.0000
7.000 0.7671 0.01586 0.01116 0.0030 0.0090 1.0000
7.250 0.7928 0.01685 0.01230 0.0032 0.0086 1.0000
7.500 0.8180 0.01795 0.01355 0.0034 0.0082 1.0000
7.750 0.8425 0.01918 0.01495 0.0036 0.0079 1.0000
8.000 0.8653 0.02108 0.01709 0.0039 0.0077 1.0000
8.250 0.8827 0.02506 0.02158 0.0042 0.0074 1.0000
8.500 0.8822 0.03516 0.03269 0.0035 0.0073 1.0000
9.250 0.6727 0.08183 0.08039 -0.0227 0.0114 1.0000
9.500 0.6530 0.09077 0.08931 -0.0257 0.0116 1.0000
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Polar data table (+)
Polar graphs
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