HT05 (ht05-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 500,000 Max Cl/Cd: 49.29 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht05-il-500000-n5.txt Download as CSV file: xf-ht05-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7687 0.11042 0.10817 0.0372 1.0000 0.0070
-10.000 -0.7739 0.10444 0.10221 0.0344 1.0000 0.0070
-9.000 -0.9186 0.03307 0.02973 -0.0101 1.0000 0.0065
-8.750 -0.9082 0.02815 0.02421 -0.0098 1.0000 0.0068
-8.500 -0.8914 0.02504 0.02065 -0.0092 1.0000 0.0071
-8.250 -0.8707 0.02308 0.01835 -0.0087 1.0000 0.0075
-8.000 -0.8480 0.02169 0.01669 -0.0082 1.0000 0.0078
-7.750 -0.8269 0.01958 0.01423 -0.0075 1.0000 0.0082
-7.500 -0.8040 0.01815 0.01259 -0.0070 1.0000 0.0087
-7.250 -0.7794 0.01725 0.01156 -0.0066 1.0000 0.0091
-7.000 -0.7545 0.01643 0.01059 -0.0062 1.0000 0.0096
-6.750 -0.7294 0.01561 0.00962 -0.0058 1.0000 0.0101
-6.500 -0.7041 0.01482 0.00869 -0.0053 1.0000 0.0108
-6.250 -0.6785 0.01410 0.00785 -0.0049 1.0000 0.0114
-6.000 -0.6525 0.01360 0.00724 -0.0045 1.0000 0.0119
-5.750 -0.6273 0.01273 0.00627 -0.0041 1.0000 0.0135
-5.500 -0.6011 0.01227 0.00576 -0.0038 1.0000 0.0146
-5.250 -0.5749 0.01179 0.00522 -0.0034 1.0000 0.0158
-5.000 -0.5485 0.01137 0.00473 -0.0030 1.0000 0.0170
-4.750 -0.5222 0.01091 0.00420 -0.0027 1.0000 0.0186
-4.500 -0.4958 0.01050 0.00378 -0.0023 1.0000 0.0218
-4.250 -0.4693 0.01020 0.00344 -0.0020 1.0000 0.0246
-4.000 -0.4428 0.00986 0.00308 -0.0016 1.0000 0.0282
-3.750 -0.4163 0.00957 0.00280 -0.0012 1.0000 0.0337
-3.500 -0.3899 0.00929 0.00253 -0.0009 1.0000 0.0419
-3.250 -0.3634 0.00904 0.00231 -0.0005 1.0000 0.0522
-3.000 -0.3371 0.00878 0.00211 -0.0001 1.0000 0.0664
-2.750 -0.3109 0.00853 0.00194 0.0003 1.0000 0.0862
-2.500 -0.2848 0.00829 0.00180 0.0007 1.0000 0.1078
-2.250 -0.2587 0.00805 0.00166 0.0011 1.0000 0.1358
-2.000 -0.2327 0.00783 0.00156 0.0015 1.0000 0.1645
-1.750 -0.1940 0.00756 0.00144 -0.0010 0.9850 0.2049
-1.500 -0.1576 0.00730 0.00133 -0.0028 0.9576 0.2505
-1.250 -0.1291 0.00730 0.00120 -0.0024 0.8195 0.2977
-1.000 -0.1078 0.00771 0.00116 -0.0009 0.6561 0.3566
-0.750 -0.0817 0.00753 0.00118 -0.0007 0.6421 0.4434
-0.500 -0.0554 0.00738 0.00126 -0.0003 0.6326 0.5313
-0.250 -0.0279 0.00733 0.00133 -0.0001 0.6219 0.5824
0.000 0.0001 0.00730 0.00135 0.0000 0.6069 0.6073
0.250 0.0281 0.00733 0.00133 0.0001 0.5824 0.6219
0.500 0.0556 0.00738 0.00126 0.0003 0.5301 0.6326
0.750 0.0819 0.00753 0.00118 0.0007 0.4421 0.6420
1.000 0.1080 0.00771 0.00116 0.0009 0.3564 0.6563
1.250 0.1293 0.00730 0.00120 0.0024 0.2974 0.8202
1.500 0.1578 0.00730 0.00133 0.0028 0.2506 0.9576
1.750 0.1942 0.00756 0.00144 0.0009 0.2045 0.9851
2.000 0.2328 0.00783 0.00156 -0.0015 0.1640 1.0000
2.250 0.2589 0.00805 0.00166 -0.0011 0.1358 1.0000
2.500 0.2849 0.00829 0.00180 -0.0007 0.1080 1.0000
2.750 0.3110 0.00853 0.00194 -0.0003 0.0862 1.0000
3.000 0.3373 0.00878 0.00211 0.0001 0.0663 1.0000
3.250 0.3636 0.00904 0.00231 0.0005 0.0522 1.0000
3.500 0.3900 0.00929 0.00253 0.0009 0.0417 1.0000
3.750 0.4164 0.00957 0.00280 0.0012 0.0336 1.0000
4.000 0.4429 0.00987 0.00308 0.0016 0.0281 1.0000
4.250 0.4694 0.01020 0.00344 0.0020 0.0245 1.0000
4.500 0.4960 0.01050 0.00377 0.0023 0.0217 1.0000
4.750 0.5223 0.01092 0.00422 0.0027 0.0185 1.0000
5.000 0.5487 0.01137 0.00473 0.0030 0.0170 1.0000
5.250 0.5750 0.01179 0.00523 0.0034 0.0158 1.0000
5.500 0.6013 0.01227 0.00577 0.0038 0.0146 1.0000
5.750 0.6274 0.01273 0.00627 0.0041 0.0134 1.0000
6.000 0.6526 0.01360 0.00724 0.0045 0.0120 1.0000
6.250 0.6787 0.01411 0.00786 0.0049 0.0114 1.0000
6.500 0.7042 0.01483 0.00870 0.0053 0.0108 1.0000
6.750 0.7295 0.01562 0.00963 0.0058 0.0102 1.0000
7.000 0.7546 0.01644 0.01059 0.0062 0.0096 1.0000
7.250 0.7795 0.01726 0.01157 0.0066 0.0091 1.0000
7.500 0.8040 0.01817 0.01261 0.0070 0.0087 1.0000
7.750 0.8269 0.01966 0.01431 0.0075 0.0082 1.0000
8.000 0.8483 0.02163 0.01662 0.0082 0.0078 1.0000
8.250 0.8709 0.02306 0.01833 0.0087 0.0075 1.0000
8.500 0.8916 0.02504 0.02064 0.0092 0.0071 1.0000
8.750 0.9082 0.02820 0.02427 0.0098 0.0068 1.0000
9.000 0.9186 0.03312 0.02979 0.0100 0.0065 1.0000
10.000 0.7741 0.10463 0.10240 -0.0346 0.0070 1.0000
10.250 0.7690 0.11061 0.10836 -0.0374 0.0069 1.0000
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Polar data table (+)
Polar graphs
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