HT22 (ht22-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 500,000 Max Cl/Cd: 60.68 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht22-il-500000.txt Download as CSV file: xf-ht22-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HT22
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6645 0.09847 0.09630 0.0323 1.0001 0.0147
-8.000 -0.6614 0.09400 0.09185 0.0290 1.0001 0.0147
-7.750 -0.6644 0.08744 0.08533 0.0245 1.0001 0.0150
-7.500 -0.6572 0.08331 0.08120 0.0215 1.0001 0.0153
-7.250 -0.6469 0.07930 0.07718 0.0181 1.0001 0.0155
-7.000 -0.6345 0.07498 0.07283 0.0141 1.0001 0.0159
-6.750 -0.6198 0.07022 0.06803 0.0093 1.0001 0.0164
-6.500 -0.6026 0.06503 0.06278 0.0043 1.0001 0.0171
-6.250 -0.5824 0.05926 0.05690 -0.0009 1.0001 0.0181
-6.000 -0.5488 0.05193 0.04926 -0.0071 1.0001 0.0200
-5.750 -0.5262 0.04631 0.04335 -0.0096 1.0001 0.0201
-5.500 -0.5134 0.03896 0.03581 -0.0122 1.0001 0.0211
-5.250 -0.4918 0.03699 0.03377 -0.0128 1.0001 0.0220
-5.000 -0.4677 0.03450 0.03113 -0.0134 1.0001 0.0239
-4.750 -0.4359 0.03273 0.02894 -0.0130 1.0001 0.0271
-4.500 -0.4137 0.02585 0.02145 -0.0140 1.0001 0.0282
-4.250 -0.3866 0.01807 0.01293 -0.0134 1.0001 0.0182
-4.000 -0.3590 0.01537 0.00980 -0.0129 1.0001 0.0183
-3.750 -0.3314 0.01381 0.00799 -0.0125 1.0001 0.0189
-3.500 -0.3034 0.01345 0.00749 -0.0122 1.0001 0.0200
-3.250 -0.2768 0.01135 0.00525 -0.0119 1.0001 0.0217
-3.000 -0.2494 0.01064 0.00451 -0.0116 1.0001 0.0233
-2.750 -0.2218 0.01005 0.00388 -0.0113 1.0001 0.0254
-2.500 -0.1941 0.00970 0.00350 -0.0111 1.0001 0.0274
-2.250 -0.1667 0.00890 0.00270 -0.0109 1.0001 0.0327
-2.000 -0.1389 0.00860 0.00238 -0.0107 1.0001 0.0368
-1.750 -0.1112 0.00812 0.00193 -0.0105 1.0001 0.0471
-1.500 -0.0834 0.00773 0.00160 -0.0103 1.0001 0.0650
-1.250 -0.0559 0.00720 0.00140 -0.0103 1.0001 0.1424
-1.000 -0.0294 0.00622 0.00127 -0.0105 1.0001 0.3875
-0.750 -0.0062 0.00497 0.00123 -0.0099 1.0001 0.7234
-0.500 0.0229 0.00429 0.00123 -0.0092 1.0001 0.9999
-0.250 0.0501 0.00430 0.00118 -0.0089 1.0001 0.9999
0.000 0.0887 0.00433 0.00116 -0.0111 0.9642 0.9999
0.250 0.1183 0.00451 0.00109 -0.0107 0.8588 0.9999
0.500 0.1400 0.00492 0.00104 -0.0088 0.7464 0.9999
0.750 0.1651 0.00533 0.00103 -0.0080 0.6506 0.9999
1.000 0.1917 0.00567 0.00104 -0.0076 0.5760 0.9999
1.250 0.2189 0.00595 0.00106 -0.0074 0.5184 0.9999
1.500 0.2463 0.00619 0.00111 -0.0072 0.4726 0.9999
1.750 0.2738 0.00642 0.00116 -0.0071 0.4345 0.9999
2.000 0.3014 0.00662 0.00123 -0.0070 0.4000 0.9999
2.250 0.3290 0.00683 0.00130 -0.0068 0.3680 0.9999
2.500 0.3566 0.00704 0.00138 -0.0067 0.3365 0.9999
3.000 0.4118 0.00749 0.00160 -0.0065 0.2734 0.9999
3.250 0.4394 0.00775 0.00173 -0.0065 0.2392 0.9999
3.500 0.4668 0.00805 0.00188 -0.0064 0.2036 0.9999
3.750 0.4941 0.00838 0.00209 -0.0063 0.1689 0.9999
4.000 0.5214 0.00875 0.00231 -0.0063 0.1369 0.9999
4.250 0.5486 0.00913 0.00257 -0.0062 0.1076 0.9999
4.500 0.5757 0.00957 0.00289 -0.0061 0.0839 0.9999
4.750 0.6029 0.00998 0.00326 -0.0060 0.0687 0.9999
5.000 0.6300 0.01049 0.00373 -0.0059 0.0575 0.9999
5.250 0.6572 0.01083 0.00409 -0.0057 0.0512 0.9999
5.500 0.6839 0.01145 0.00474 -0.0055 0.0453 0.9999
5.750 0.7109 0.01186 0.00521 -0.0053 0.0421 0.9999
6.000 0.7376 0.01237 0.00575 -0.0051 0.0389 0.9999
6.250 0.7627 0.01357 0.00703 -0.0048 0.0356 0.9999
6.500 0.7895 0.01393 0.00748 -0.0046 0.0342 0.9999
6.750 0.8158 0.01453 0.00817 -0.0043 0.0324 0.9999
7.000 0.8418 0.01520 0.00891 -0.0040 0.0308 0.9999
7.250 0.8674 0.01594 0.00971 -0.0038 0.0292 0.9999
7.500 0.8897 0.01807 0.01200 -0.0033 0.0270 0.9999
7.750 0.9151 0.01884 0.01293 -0.0030 0.0262 0.9999
8.000 0.9402 0.01975 0.01401 -0.0026 0.0253 0.9999
8.250 0.9645 0.02090 0.01533 -0.0023 0.0242 0.9999
8.500 0.9886 0.02190 0.01647 -0.0020 0.0230 0.9999
8.750 1.0129 0.02260 0.01727 -0.0017 0.0218 0.9999
9.000 1.0347 0.02412 0.01891 -0.0015 0.0207 0.9999
9.250 1.0475 0.02877 0.02408 -0.0009 0.0197 0.9999
9.500 1.0683 0.03026 0.02584 -0.0006 0.0192 0.9999
9.750 1.0850 0.03279 0.02872 -0.0002 0.0185 0.9999
10.000 1.0990 0.03564 0.03192 0.0000 0.0178 0.9999
10.250 1.1128 0.03807 0.03461 0.0000 0.0170 0.9999
10.500 1.1280 0.03981 0.03651 0.0000 0.0163 0.9999
10.750 1.1383 0.04225 0.03916 -0.0002 0.0158 0.9999
11.000 1.1438 0.04524 0.04235 -0.0008 0.0155 0.9999
11.250 1.1369 0.04990 0.04726 -0.0027 0.0153 0.9999
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Polar data table (+)
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