HT05 (ht05-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 200,000 Max Cl/Cd: 34.57 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht05-il-200000-n5.txt Download as CSV file: xf-ht05-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT05
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7447 0.09428 0.09080 0.0260 1.0000 0.0150
-8.750 -0.7494 0.08864 0.08521 0.0224 1.0000 0.0149
-8.500 -0.7559 0.08258 0.07919 0.0176 1.0000 0.0147
-8.250 -0.7584 0.07508 0.07168 0.0108 1.0000 0.0145
-8.000 -0.7589 0.06510 0.06162 0.0019 1.0000 0.0143
-7.750 -0.7626 0.05111 0.04727 -0.0062 1.0000 0.0140
-7.500 -0.7640 0.03920 0.03459 -0.0092 1.0000 0.0140
-7.250 -0.7524 0.03315 0.02785 -0.0094 1.0000 0.0143
-7.000 -0.7352 0.02900 0.02309 -0.0089 1.0000 0.0150
-6.750 -0.7144 0.02615 0.01971 -0.0083 1.0000 0.0160
-6.500 -0.6911 0.02435 0.01746 -0.0077 1.0000 0.0173
-6.250 -0.6688 0.02180 0.01450 -0.0070 1.0000 0.0183
-6.000 -0.6450 0.02012 0.01261 -0.0064 1.0000 0.0193
-5.750 -0.6203 0.01892 0.01121 -0.0059 1.0000 0.0205
-5.500 -0.5953 0.01779 0.00991 -0.0053 1.0000 0.0221
-5.250 -0.5697 0.01699 0.00894 -0.0048 1.0000 0.0245
-5.000 -0.5447 0.01588 0.00772 -0.0042 1.0000 0.0269
-4.750 -0.5194 0.01503 0.00680 -0.0037 1.0000 0.0296
-4.500 -0.4937 0.01436 0.00602 -0.0032 1.0000 0.0330
-4.250 -0.4679 0.01372 0.00532 -0.0028 1.0000 0.0383
-4.000 -0.4420 0.01318 0.00475 -0.0023 1.0000 0.0449
-3.750 -0.4160 0.01264 0.00420 -0.0019 1.0000 0.0541
-3.500 -0.3900 0.01217 0.00375 -0.0015 1.0000 0.0689
-3.250 -0.3640 0.01175 0.00337 -0.0010 1.0000 0.0879
-3.000 -0.3381 0.01133 0.00308 -0.0007 1.0000 0.1176
-2.750 -0.3122 0.01096 0.00284 -0.0003 1.0000 0.1510
-2.500 -0.2863 0.01060 0.00263 0.0001 1.0000 0.1904
-2.250 -0.2605 0.01024 0.00243 0.0005 1.0000 0.2346
-2.000 -0.2350 0.00987 0.00227 0.0010 1.0000 0.2874
-1.750 -0.2098 0.00945 0.00214 0.0015 1.0000 0.3594
-1.500 -0.1854 0.00896 0.00209 0.0021 1.0000 0.4647
-1.250 -0.1610 0.00863 0.00208 0.0030 1.0000 0.5628
-1.000 -0.1350 0.00851 0.00202 0.0036 1.0000 0.6137
-0.750 -0.1095 0.00827 0.00188 0.0042 1.0000 0.6421
-0.500 -0.0878 0.00761 0.00181 0.0059 1.0000 0.7156
-0.250 -0.0330 0.00738 0.00203 0.0011 1.0000 0.9869
0.000 0.0001 0.00739 0.00203 0.0000 1.0000 1.0000
0.250 0.0332 0.00738 0.00203 -0.0011 0.9868 1.0000
0.500 0.0878 0.00762 0.00180 -0.0059 0.7120 1.0000
0.750 0.1096 0.00827 0.00188 -0.0042 0.6419 1.0000
1.000 0.1352 0.00851 0.00202 -0.0036 0.6135 1.0000
1.250 0.1611 0.00863 0.00208 -0.0030 0.5622 1.0000
1.500 0.1856 0.00896 0.00209 -0.0021 0.4640 1.0000
1.750 0.2099 0.00945 0.00214 -0.0015 0.3592 1.0000
2.000 0.2351 0.00987 0.00227 -0.0010 0.2874 1.0000
2.250 0.2607 0.01024 0.00243 -0.0005 0.2345 1.0000
2.500 0.2864 0.01060 0.00263 -0.0001 0.1900 1.0000
2.750 0.3123 0.01096 0.00284 0.0003 0.1508 1.0000
3.000 0.3382 0.01133 0.00308 0.0007 0.1175 1.0000
3.250 0.3641 0.01175 0.00337 0.0010 0.0879 1.0000
3.500 0.3902 0.01217 0.00375 0.0015 0.0688 1.0000
3.750 0.4162 0.01264 0.00421 0.0019 0.0539 1.0000
4.000 0.4421 0.01318 0.00475 0.0023 0.0449 1.0000
4.250 0.4681 0.01373 0.00533 0.0028 0.0382 1.0000
4.500 0.4938 0.01436 0.00602 0.0032 0.0329 1.0000
4.750 0.5196 0.01503 0.00680 0.0037 0.0295 1.0000
5.000 0.5448 0.01591 0.00774 0.0042 0.0269 1.0000
5.250 0.5699 0.01698 0.00894 0.0048 0.0245 1.0000
5.500 0.5954 0.01780 0.00992 0.0053 0.0221 1.0000
5.750 0.6205 0.01892 0.01121 0.0059 0.0205 1.0000
6.000 0.6452 0.02013 0.01261 0.0064 0.0193 1.0000
6.250 0.6688 0.02187 0.01457 0.0070 0.0183 1.0000
6.500 0.6913 0.02433 0.01745 0.0077 0.0173 1.0000
6.750 0.7146 0.02615 0.01971 0.0083 0.0159 1.0000
7.000 0.7353 0.02905 0.02314 0.0089 0.0150 1.0000
7.250 0.7525 0.03317 0.02788 0.0094 0.0144 1.0000
7.500 0.7643 0.03918 0.03457 0.0092 0.0140 1.0000
7.750 0.7628 0.05111 0.04727 0.0062 0.0140 1.0000
8.000 0.7590 0.06520 0.06172 -0.0020 0.0143 1.0000
8.250 0.7586 0.07519 0.07179 -0.0109 0.0146 1.0000
8.500 0.7561 0.08268 0.07929 -0.0178 0.0148 1.0000
8.750 0.7496 0.08876 0.08533 -0.0226 0.0149 1.0000
9.000 0.7451 0.09440 0.09092 -0.0262 0.0151 1.0000
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Polar data table (+)
Polar graphs
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