HT08 (ht08-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: HT08 (ht08-il) Reynolds number: 200,000 Max Cl/Cd: 33.1 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht08-il-200000.txt Download as CSV file: xf-ht08-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7468 0.11544 0.11203 0.0334 1.0000 0.0430
-9.250 -0.7467 0.11058 0.10719 0.0296 1.0000 0.0431
-9.000 -0.7525 0.10346 0.10013 0.0286 1.0000 0.0438
-8.750 -0.7458 0.10015 0.09680 0.0313 1.0000 0.0449
-8.500 -0.7411 0.09668 0.09334 0.0311 1.0000 0.0460
-8.250 -0.7389 0.09274 0.08942 0.0293 1.0000 0.0471
-8.000 -0.7383 0.08828 0.08499 0.0260 1.0000 0.0482
-7.750 -0.7344 0.08284 0.07955 0.0203 1.0000 0.0497
-7.500 -0.7280 0.07642 0.07308 0.0131 1.0000 0.0517
-7.250 -0.7179 0.06734 0.06343 -0.0009 1.0000 0.0553
-7.000 -0.7137 0.05912 0.05517 -0.0029 1.0000 0.0566
-6.750 -0.6991 0.05587 0.05195 -0.0025 1.0000 0.0581
-6.500 -0.6829 0.05245 0.04845 -0.0031 1.0000 0.0605
-6.250 -0.6658 0.04638 0.04153 -0.0065 1.0000 0.0692
-6.000 -0.6449 0.03439 0.02884 -0.0065 1.0000 0.0410
-5.750 -0.6229 0.02951 0.02340 -0.0065 1.0000 0.0396
-5.500 -0.5984 0.02482 0.01804 -0.0060 1.0000 0.0375
-5.250 -0.5720 0.02183 0.01452 -0.0055 1.0000 0.0378
-5.000 -0.5451 0.01982 0.01215 -0.0050 1.0000 0.0397
-4.750 -0.5173 0.01900 0.01103 -0.0045 1.0000 0.0430
-4.500 -0.4914 0.01641 0.00828 -0.0041 1.0000 0.0463
-4.250 -0.4645 0.01533 0.00715 -0.0037 1.0000 0.0512
-4.000 -0.4379 0.01420 0.00598 -0.0034 1.0000 0.0588
-3.750 -0.4107 0.01342 0.00514 -0.0030 1.0000 0.0681
-3.500 -0.3842 0.01240 0.00425 -0.0028 1.0000 0.0864
-3.250 -0.3572 0.01155 0.00352 -0.0026 1.0000 0.1220
-3.000 -0.3308 0.01060 0.00303 -0.0027 1.0000 0.2024
-2.750 -0.3047 0.00979 0.00272 -0.0026 1.0000 0.3181
-2.500 -0.2795 0.00896 0.00249 -0.0024 1.0000 0.4601
-2.250 -0.2574 0.00801 0.00233 -0.0010 1.0000 0.6456
-2.000 -0.2409 0.00728 0.00231 0.0027 1.0000 0.8419
-1.750 -0.1841 0.00710 0.00219 -0.0024 1.0000 0.9998
-1.500 -0.1580 0.00704 0.00201 -0.0020 1.0000 1.0000
-1.250 -0.1319 0.00699 0.00185 -0.0017 1.0000 1.0000
-1.000 -0.1057 0.00696 0.00173 -0.0013 1.0000 1.0000
-0.750 -0.0793 0.00693 0.00165 -0.0010 1.0000 1.0000
-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 0.0795 0.00693 0.00165 0.0010 1.0000 1.0000
1.000 0.1058 0.00696 0.00173 0.0013 1.0000 1.0000
1.250 0.1321 0.00699 0.00185 0.0017 1.0000 1.0000
1.500 0.1582 0.00704 0.00201 0.0020 1.0000 1.0000
1.750 0.1845 0.00710 0.00219 0.0023 0.9994 1.0000
2.000 0.2410 0.00728 0.00231 -0.0027 0.8412 1.0000
2.250 0.2575 0.00802 0.00233 0.0010 0.6447 1.0000
2.500 0.2797 0.00896 0.00249 0.0024 0.4592 1.0000
2.750 0.3048 0.00979 0.00272 0.0026 0.3172 1.0000
3.000 0.3309 0.01061 0.00303 0.0027 0.2019 1.0000
3.250 0.3573 0.01156 0.00353 0.0026 0.1217 1.0000
3.500 0.3843 0.01240 0.00426 0.0028 0.0863 1.0000
3.750 0.4108 0.01342 0.00515 0.0030 0.0681 1.0000
4.000 0.4380 0.01421 0.00599 0.0034 0.0588 1.0000
4.250 0.4647 0.01533 0.00715 0.0037 0.0512 1.0000
4.500 0.4916 0.01642 0.00829 0.0041 0.0462 1.0000
4.750 0.5175 0.01901 0.01104 0.0045 0.0430 1.0000
5.000 0.5453 0.01984 0.01217 0.0050 0.0397 1.0000
5.250 0.5722 0.02185 0.01454 0.0055 0.0378 1.0000
5.500 0.5986 0.02485 0.01806 0.0060 0.0375 1.0000
5.750 0.6231 0.02954 0.02344 0.0065 0.0397 1.0000
6.000 0.6449 0.03447 0.02891 0.0065 0.0411 1.0000
6.250 0.6660 0.04641 0.04156 0.0065 0.0692 1.0000
6.500 0.6831 0.05248 0.04848 0.0030 0.0605 1.0000
6.750 0.6993 0.05590 0.05198 0.0024 0.0581 1.0000
7.000 0.7139 0.05915 0.05521 0.0028 0.0566 1.0000
7.250 0.7181 0.06738 0.06347 0.0008 0.0553 1.0000
7.500 0.7283 0.07648 0.07314 -0.0132 0.0517 1.0000
7.750 0.7348 0.08289 0.07960 -0.0204 0.0497 1.0000
8.000 0.7388 0.08833 0.08504 -0.0261 0.0482 1.0000
8.250 0.7394 0.09278 0.08946 -0.0294 0.0470 1.0000
8.500 0.7417 0.09672 0.09338 -0.0312 0.0460 1.0000
8.750 0.7465 0.10016 0.09682 -0.0313 0.0449 1.0000
9.000 0.7533 0.10351 0.10018 -0.0283 0.0438 1.0000
9.250 0.6069 0.10119 0.09789 -0.0259 0.0485 1.0000
9.500 0.6065 0.10531 0.10199 -0.0268 0.0472 1.0000
|
Polar data table (+)
Polar graphs
<< Back to HT08 (ht08-il)