HT22 (ht22-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT22 (ht22-il) Reynolds number: 500,000 Max Cl/Cd: 63.19 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht22-il-500000-n5.txt Download as CSV file: xf-ht22-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6856 0.11242 0.11017 0.0445 1.0001 0.0073
-9.000 -0.6825 0.10860 0.10636 0.0429 1.0001 0.0072
-8.750 -0.6801 0.10453 0.10230 0.0410 1.0001 0.0070
-8.500 -0.6781 0.10032 0.09811 0.0389 1.0001 0.0069
-8.250 -0.6767 0.09597 0.09378 0.0364 1.0001 0.0068
-8.000 -0.6755 0.09149 0.08932 0.0336 1.0001 0.0068
-7.750 -0.6739 0.08662 0.08447 0.0294 1.0001 0.0067
-7.500 -0.6666 0.08072 0.07857 0.0228 1.0001 0.0067
-7.250 -0.6561 0.07407 0.07190 0.0152 1.0001 0.0067
-7.000 -0.6423 0.06654 0.06430 0.0073 1.0001 0.0068
-6.750 -0.6257 0.05833 0.05595 -0.0001 1.0001 0.0070
-6.500 -0.6070 0.04952 0.04691 -0.0062 1.0001 0.0071
-6.250 -0.5875 0.03763 0.03452 -0.0112 1.0001 0.0074
-6.000 -0.5723 0.02058 0.01594 -0.0135 1.0001 0.0079
-5.750 -0.5470 0.01834 0.01333 -0.0134 1.0001 0.0082
-5.500 -0.5209 0.01683 0.01156 -0.0133 1.0001 0.0085
-5.250 -0.4944 0.01548 0.00996 -0.0131 1.0001 0.0089
-5.000 -0.4677 0.01427 0.00851 -0.0128 1.0001 0.0095
-4.750 -0.4407 0.01323 0.00728 -0.0125 1.0001 0.0100
-4.500 -0.4136 0.01242 0.00631 -0.0123 1.0001 0.0105
-4.250 -0.3866 0.01158 0.00536 -0.0121 1.0001 0.0111
-4.000 -0.3593 0.01117 0.00494 -0.0119 1.0001 0.0121
-3.750 -0.3319 0.01076 0.00449 -0.0117 1.0001 0.0131
-3.500 -0.3044 0.01024 0.00391 -0.0115 1.0001 0.0141
-3.250 -0.2769 0.00976 0.00338 -0.0113 1.0001 0.0150
-3.000 -0.2493 0.00931 0.00292 -0.0112 1.0001 0.0166
-2.750 -0.2217 0.00903 0.00264 -0.0110 1.0001 0.0187
-2.500 -0.1940 0.00872 0.00232 -0.0108 1.0001 0.0214
-2.250 -0.1662 0.00844 0.00206 -0.0107 1.0001 0.0247
-2.000 -0.1385 0.00821 0.00182 -0.0105 1.0001 0.0287
-1.750 -0.1108 0.00799 0.00165 -0.0104 1.0001 0.0359
-1.500 -0.0797 0.00778 0.00149 -0.0110 0.9803 0.0469
-1.250 -0.0448 0.00763 0.00134 -0.0122 0.9015 0.0694
-1.000 -0.0229 0.00770 0.00123 -0.0104 0.8077 0.1029
-0.750 0.0017 0.00770 0.00113 -0.0096 0.7200 0.1724
-0.500 0.0277 0.00750 0.00105 -0.0093 0.6444 0.2987
-0.250 0.0539 0.00712 0.00100 -0.0093 0.5815 0.4794
0.000 0.0793 0.00663 0.00099 -0.0089 0.5305 0.6769
0.250 0.0982 0.00608 0.00100 -0.0064 0.4924 0.8867
0.500 0.1336 0.00612 0.00097 -0.0078 0.4516 0.9999
0.750 0.1612 0.00629 0.00097 -0.0076 0.4206 0.9999
1.250 0.2167 0.00660 0.00101 -0.0074 0.3651 0.9999
1.500 0.2445 0.00676 0.00104 -0.0073 0.3386 0.9999
1.750 0.2722 0.00693 0.00110 -0.0072 0.3122 0.9999
2.000 0.2999 0.00712 0.00116 -0.0071 0.2844 0.9999
2.250 0.3276 0.00732 0.00123 -0.0070 0.2560 0.9999
2.500 0.3553 0.00754 0.00132 -0.0069 0.2266 0.9999
2.750 0.3829 0.00777 0.00145 -0.0068 0.1997 0.9999
3.000 0.4104 0.00802 0.00158 -0.0068 0.1713 0.9999
3.250 0.4379 0.00829 0.00173 -0.0067 0.1454 0.9999
3.500 0.4654 0.00858 0.00190 -0.0066 0.1210 0.9999
3.750 0.4929 0.00886 0.00211 -0.0065 0.1005 0.9999
4.000 0.5203 0.00915 0.00232 -0.0065 0.0841 0.9999
4.250 0.5477 0.00945 0.00255 -0.0064 0.0698 0.9999
4.500 0.5750 0.00975 0.00282 -0.0063 0.0584 0.9999
4.750 0.6024 0.01002 0.00308 -0.0062 0.0512 0.9999
5.000 0.6297 0.01033 0.00338 -0.0060 0.0450 0.9999
5.250 0.6569 0.01063 0.00369 -0.0059 0.0402 0.9999
5.500 0.6840 0.01101 0.00408 -0.0058 0.0353 0.9999
5.750 0.7111 0.01132 0.00444 -0.0056 0.0329 0.9999
6.000 0.7381 0.01168 0.00483 -0.0055 0.0304 0.9999
6.250 0.7648 0.01214 0.00531 -0.0053 0.0279 0.9999
6.500 0.7914 0.01263 0.00588 -0.0051 0.0263 0.9999
6.750 0.8181 0.01302 0.00634 -0.0050 0.0250 0.9999
7.000 0.8446 0.01345 0.00683 -0.0048 0.0236 0.9999
7.250 0.8709 0.01393 0.00737 -0.0046 0.0223 0.9999
7.500 0.8968 0.01452 0.00803 -0.0044 0.0211 0.9999
7.750 0.9218 0.01539 0.00899 -0.0042 0.0197 0.9999
8.000 0.9478 0.01586 0.00957 -0.0040 0.0190 0.9999
8.250 0.9733 0.01647 0.01028 -0.0037 0.0182 0.9999
8.500 0.9985 0.01713 0.01106 -0.0035 0.0174 0.9999
8.750 1.0235 0.01779 0.01183 -0.0032 0.0166 0.9999
9.000 1.0485 0.01842 0.01254 -0.0030 0.0157 0.9999
9.250 1.0719 0.01942 0.01363 -0.0028 0.0148 0.9999
9.500 1.0954 0.02040 0.01476 -0.0025 0.0142 0.9999
9.750 1.1189 0.02131 0.01585 -0.0021 0.0137 0.9999
10.000 1.1417 0.02233 0.01706 -0.0018 0.0131 0.9999
10.250 1.1641 0.02338 0.01828 -0.0015 0.0125 0.9999
10.500 1.1865 0.02432 0.01936 -0.0012 0.0119 0.9999
10.750 1.2089 0.02517 0.02032 -0.0010 0.0114 0.9999
11.000 1.2297 0.02631 0.02157 -0.0007 0.0108 0.9999
11.250 1.2468 0.02817 0.02364 -0.0004 0.0103 0.9999
11.500 1.2643 0.02983 0.02555 0.0000 0.0100 0.9999
11.750 1.2796 0.03178 0.02778 0.0003 0.0097 0.9999
12.000 1.2925 0.03399 0.03024 0.0005 0.0094 0.9999
12.250 1.3025 0.03644 0.03294 0.0006 0.0090 0.9999
12.500 1.3092 0.03917 0.03590 0.0004 0.0088 0.9999
12.750 1.3111 0.04236 0.03933 -0.0003 0.0086 0.9999
13.000 1.2965 0.04785 0.04507 -0.0042 0.0085 0.9999
13.250 1.2447 0.06728 0.06488 -0.0239 0.0089 0.9999
13.500 1.1810 0.08528 0.08302 -0.0356 0.0094 0.9999
13.750 1.1173 0.10295 0.10077 -0.0456 0.0099 0.9999
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