HT05 (ht05-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 1,000,000 Max Cl/Cd: 57.72 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht05-il-1000000.txt Download as CSV file: xf-ht05-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7480 0.13263 0.13101 0.0465 1.0000 0.0106
-10.750 -0.7462 0.12745 0.12584 0.0439 1.0000 0.0114
-8.750 -0.8935 0.03272 0.03017 -0.0099 1.0000 0.0074
-8.500 -0.8821 0.02810 0.02506 -0.0096 1.0000 0.0076
-8.250 -0.8639 0.02548 0.02211 -0.0091 1.0000 0.0078
-8.000 -0.8416 0.02411 0.02053 -0.0087 1.0000 0.0079
-7.750 -0.8289 0.01885 0.01455 -0.0075 1.0000 0.0082
-7.500 -0.8084 0.01630 0.01165 -0.0066 1.0000 0.0086
-7.250 -0.7839 0.01532 0.01055 -0.0062 1.0000 0.0091
-7.000 -0.7582 0.01476 0.00991 -0.0059 1.0000 0.0096
-6.750 -0.7322 0.01431 0.00939 -0.0056 1.0000 0.0103
-6.500 -0.7063 0.01368 0.00867 -0.0052 1.0000 0.0111
-6.250 -0.6803 0.01306 0.00795 -0.0049 1.0000 0.0116
-6.000 -0.6538 0.01264 0.00746 -0.0045 1.0000 0.0119
-5.750 -0.6299 0.01099 0.00557 -0.0038 1.0000 0.0131
-5.500 -0.6036 0.01045 0.00499 -0.0035 1.0000 0.0143
-5.250 -0.5769 0.01010 0.00461 -0.0032 1.0000 0.0155
-5.000 -0.5501 0.00983 0.00431 -0.0029 1.0000 0.0169
-4.750 -0.5231 0.00963 0.00409 -0.0026 1.0000 0.0176
-4.500 -0.4971 0.00883 0.00317 -0.0021 1.0000 0.0211
-4.250 -0.4703 0.00856 0.00289 -0.0018 1.0000 0.0238
-4.000 -0.4434 0.00838 0.00271 -0.0015 1.0000 0.0256
-3.750 -0.4169 0.00797 0.00230 -0.0011 1.0000 0.0336
-3.500 -0.3903 0.00770 0.00204 -0.0007 1.0000 0.0422
-3.250 -0.3639 0.00744 0.00185 -0.0004 1.0000 0.0552
-3.000 -0.3376 0.00721 0.00169 0.0000 1.0000 0.0733
-2.750 -0.3115 0.00695 0.00155 0.0005 1.0000 0.0991
-2.500 -0.2855 0.00673 0.00143 0.0009 1.0000 0.1267
-2.250 -0.2596 0.00651 0.00133 0.0014 1.0000 0.1583
-2.000 -0.2314 0.00629 0.00124 0.0013 0.9991 0.1907
-1.750 -0.1950 0.00602 0.00115 -0.0007 0.9943 0.2380
-1.500 -0.1608 0.00574 0.00106 -0.0021 0.9837 0.2937
-1.250 -0.1277 0.00540 0.00099 -0.0033 0.9628 0.3746
-1.000 -0.1024 0.00513 0.00094 -0.0025 0.9002 0.4761
-0.750 -0.0831 0.00574 0.00096 -0.0005 0.6630 0.5492
-0.500 -0.0557 0.00584 0.00106 -0.0003 0.6476 0.5962
-0.250 -0.0278 0.00598 0.00113 -0.0001 0.6374 0.6155
0.000 0.0001 0.00606 0.00117 0.0000 0.6276 0.6278
0.250 0.0280 0.00598 0.00113 0.0001 0.6152 0.6374
0.500 0.0559 0.00584 0.00106 0.0003 0.5959 0.6476
0.750 0.0833 0.00574 0.00096 0.0004 0.5496 0.6633
1.000 0.1026 0.00513 0.00094 0.0025 0.4761 0.8997
1.250 0.1279 0.00540 0.00099 0.0033 0.3750 0.9626
1.500 0.1611 0.00575 0.00107 0.0021 0.2925 0.9840
1.750 0.1952 0.00602 0.00115 0.0007 0.2380 0.9943
2.000 0.2315 0.00629 0.00124 -0.0013 0.1908 0.9991
2.250 0.2597 0.00651 0.00133 -0.0014 0.1582 1.0000
2.500 0.2856 0.00673 0.00144 -0.0009 0.1264 1.0000
2.750 0.3116 0.00695 0.00155 -0.0005 0.0991 1.0000
3.000 0.3377 0.00721 0.00169 0.0000 0.0732 1.0000
3.250 0.3640 0.00745 0.00185 0.0004 0.0552 1.0000
3.500 0.3905 0.00770 0.00204 0.0007 0.0421 1.0000
3.750 0.4171 0.00797 0.00230 0.0011 0.0336 1.0000
4.000 0.4436 0.00838 0.00270 0.0015 0.0257 1.0000
4.250 0.4705 0.00855 0.00289 0.0018 0.0237 1.0000
4.500 0.4973 0.00883 0.00318 0.0021 0.0210 1.0000
4.750 0.5233 0.00961 0.00407 0.0026 0.0177 1.0000
5.000 0.5503 0.00982 0.00430 0.0029 0.0169 1.0000
5.250 0.5771 0.01009 0.00459 0.0032 0.0155 1.0000
5.500 0.6038 0.01046 0.00500 0.0035 0.0143 1.0000
5.750 0.6300 0.01102 0.00560 0.0038 0.0131 1.0000
6.000 0.6540 0.01265 0.00747 0.0045 0.0119 1.0000
6.250 0.6804 0.01306 0.00795 0.0049 0.0116 1.0000
6.500 0.7064 0.01369 0.00868 0.0052 0.0111 1.0000
6.750 0.7324 0.01428 0.00936 0.0056 0.0103 1.0000
7.000 0.7584 0.01474 0.00988 0.0059 0.0096 1.0000
7.250 0.7840 0.01531 0.01054 0.0062 0.0091 1.0000
7.500 0.8084 0.01635 0.01170 0.0066 0.0087 1.0000
7.750 0.8285 0.01904 0.01476 0.0075 0.0082 1.0000
8.000 0.8426 0.02378 0.02017 0.0086 0.0079 1.0000
8.250 0.8643 0.02538 0.02200 0.0091 0.0078 1.0000
8.500 0.8828 0.02791 0.02485 0.0096 0.0076 1.0000
8.750 0.8941 0.03260 0.03004 0.0099 0.0074 1.0000
11.500 0.6005 0.12958 0.12804 -0.0291 0.0119 1.0000
11.750 0.6004 0.13354 0.13200 -0.0302 0.0118 1.0000
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Polar data table (+)
Polar graphs
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