HT08 (ht08-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT08 (ht08-il) Reynolds number: 200,000 Max Cl/Cd: 34.19 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht08-il-200000-n5.txt Download as CSV file: xf-ht08-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7631 0.09521 0.09179 0.0327 1.0000 0.0146
-8.750 -0.7667 0.08966 0.08627 0.0292 1.0000 0.0144
-8.500 -0.7715 0.08369 0.08035 0.0245 1.0000 0.0143
-8.250 -0.7733 0.07619 0.07285 0.0166 1.0000 0.0141
-8.000 -0.7720 0.06716 0.06372 0.0081 1.0000 0.0139
-7.750 -0.7697 0.05687 0.05320 0.0012 1.0000 0.0137
-7.500 -0.7669 0.04593 0.04177 -0.0033 1.0000 0.0136
-7.250 -0.7586 0.03699 0.03209 -0.0052 1.0000 0.0138
-7.000 -0.7426 0.03102 0.02534 -0.0055 1.0000 0.0142
-6.750 -0.7216 0.02714 0.02079 -0.0054 1.0000 0.0149
-6.500 -0.6985 0.02447 0.01760 -0.0052 1.0000 0.0161
-6.250 -0.6743 0.02280 0.01574 -0.0051 1.0000 0.0173
-6.000 -0.6491 0.02111 0.01377 -0.0048 1.0000 0.0182
-5.750 -0.6234 0.01957 0.01196 -0.0044 1.0000 0.0193
-5.500 -0.5973 0.01819 0.01033 -0.0041 1.0000 0.0207
-5.250 -0.5707 0.01733 0.00927 -0.0038 1.0000 0.0225
-5.000 -0.5451 0.01601 0.00790 -0.0036 1.0000 0.0252
-4.750 -0.5186 0.01516 0.00697 -0.0033 1.0000 0.0276
-4.500 -0.4918 0.01441 0.00611 -0.0030 1.0000 0.0306
-4.250 -0.4651 0.01367 0.00531 -0.0029 1.0000 0.0356
-4.000 -0.4379 0.01311 0.00467 -0.0027 1.0000 0.0413
-3.750 -0.4108 0.01252 0.00409 -0.0026 1.0000 0.0501
-3.500 -0.3836 0.01202 0.00361 -0.0025 1.0000 0.0642
-3.250 -0.3564 0.01154 0.00318 -0.0024 1.0000 0.0851
-3.000 -0.3293 0.01108 0.00286 -0.0023 1.0000 0.1193
-2.750 -0.3022 0.01062 0.00258 -0.0023 1.0000 0.1643
-2.500 -0.2752 0.01015 0.00235 -0.0023 1.0000 0.2229
-2.250 -0.2484 0.00968 0.00214 -0.0022 1.0000 0.2937
-2.000 -0.2218 0.00918 0.00198 -0.0021 1.0000 0.3788
-1.750 -0.1959 0.00863 0.00185 -0.0019 1.0000 0.4829
-1.500 -0.1715 0.00800 0.00176 -0.0011 1.0000 0.6135
-1.250 -0.1504 0.00740 0.00172 0.0009 1.0000 0.7585
-1.000 -0.1262 0.00705 0.00173 0.0028 1.0000 0.8983
-0.750 -0.0805 0.00693 0.00165 -0.0007 1.0000 0.9960
-0.500 -0.0529 0.00691 0.00159 -0.0006 1.0000 1.0000
-0.250 -0.0264 0.00690 0.00154 -0.0003 1.0000 1.0000
0.000 0.0001 0.00689 0.00153 0.0000 1.0000 1.0000
0.250 0.0266 0.00690 0.00154 0.0003 1.0000 1.0000
0.500 0.0530 0.00691 0.00159 0.0006 1.0000 1.0000
0.750 0.0808 0.00693 0.00165 0.0007 0.9957 1.0000
1.000 0.1264 0.00705 0.00173 -0.0028 0.8976 1.0000
1.250 0.1505 0.00740 0.00172 -0.0009 0.7581 1.0000
1.500 0.1716 0.00800 0.00176 0.0011 0.6126 1.0000
1.750 0.1960 0.00863 0.00185 0.0019 0.4824 1.0000
2.000 0.2219 0.00918 0.00198 0.0021 0.3785 1.0000
2.250 0.2485 0.00968 0.00214 0.0022 0.2934 1.0000
2.500 0.2753 0.01015 0.00235 0.0023 0.2225 1.0000
2.750 0.3023 0.01062 0.00258 0.0023 0.1639 1.0000
3.000 0.3294 0.01108 0.00286 0.0023 0.1191 1.0000
3.250 0.3565 0.01155 0.00319 0.0024 0.0850 1.0000
3.500 0.3838 0.01202 0.00362 0.0024 0.0641 1.0000
3.750 0.4110 0.01252 0.00409 0.0026 0.0501 1.0000
4.000 0.4381 0.01311 0.00468 0.0027 0.0413 1.0000
4.250 0.4652 0.01367 0.00531 0.0029 0.0356 1.0000
4.500 0.4919 0.01442 0.00611 0.0030 0.0305 1.0000
4.750 0.5187 0.01517 0.00697 0.0033 0.0275 1.0000
5.000 0.5453 0.01602 0.00790 0.0035 0.0252 1.0000
5.250 0.5709 0.01734 0.00928 0.0038 0.0225 1.0000
5.500 0.5975 0.01820 0.01034 0.0041 0.0206 1.0000
5.750 0.6236 0.01957 0.01197 0.0044 0.0193 1.0000
6.000 0.6493 0.02112 0.01378 0.0048 0.0181 1.0000
6.250 0.6745 0.02282 0.01576 0.0050 0.0173 1.0000
6.500 0.6987 0.02448 0.01761 0.0051 0.0162 1.0000
6.750 0.7218 0.02717 0.02082 0.0053 0.0149 1.0000
7.000 0.7428 0.03104 0.02536 0.0055 0.0142 1.0000
7.250 0.7588 0.03704 0.03214 0.0051 0.0138 1.0000
7.500 0.7671 0.04599 0.04183 0.0032 0.0136 1.0000
7.750 0.7700 0.05694 0.05327 -0.0012 0.0137 1.0000
8.000 0.7723 0.06723 0.06380 -0.0082 0.0139 1.0000
8.250 0.7736 0.07628 0.07294 -0.0167 0.0141 1.0000
8.500 0.7719 0.08377 0.08042 -0.0246 0.0143 1.0000
8.750 0.7671 0.08974 0.08635 -0.0293 0.0144 1.0000
9.000 0.7636 0.09531 0.09188 -0.0329 0.0146 1.0000
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Polar data table (+)
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