CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 50,000 Max Cl/Cd: 9.9 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cap21c-il-50000.txt Download as CSV file: xf-cap21c-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: CAP 21 (TraCFoil)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5023 0.13312 0.12483 0.0354 1.0005 0.3214
-9.750 -0.4690 0.12766 0.11935 0.0360 1.0005 0.3274
-9.500 -0.4891 0.12707 0.11881 0.0347 1.0005 0.3368
-9.250 -0.4537 0.12169 0.11343 0.0354 1.0005 0.3436
-9.000 -0.4587 0.11959 0.11139 0.0348 1.0005 0.3539
-8.750 -0.4565 0.11768 0.10951 0.0349 1.0005 0.3668
-8.500 -0.4283 0.11315 0.10503 0.0353 1.0005 0.3755
-8.250 -0.4283 0.11070 0.10263 0.0350 1.0005 0.3859
-8.000 -0.4406 0.10977 0.10176 0.0350 1.0005 0.3986
-7.750 -0.4022 0.10475 0.09678 0.0353 1.0005 0.4073
-7.500 -0.3947 0.10205 0.09414 0.0355 1.0005 0.4193
-7.000 -0.3768 0.09701 0.08924 0.0364 1.0005 0.4486
-6.500 -0.3594 0.09218 0.08453 0.0374 1.0005 0.4782
-6.000 -0.3353 0.08717 0.07971 0.0386 1.0005 0.5091
-5.750 -0.3136 0.08431 0.07695 0.0391 1.0005 0.5269
-5.500 -0.2948 0.08188 0.07464 0.0399 1.0005 0.5481
-5.250 -0.2929 0.08031 0.07323 0.0415 1.0005 0.5703
-5.000 -0.2657 0.07721 0.07030 0.0415 1.0005 0.5886
-4.750 -0.2438 0.07470 0.06801 0.0417 1.0005 0.6092
-4.500 -0.2313 0.07274 0.06633 0.0426 1.0005 0.6334
-4.250 -0.1927 0.07024 0.06393 0.0403 0.7549 0.6647
-4.000 -0.1854 0.07008 0.06280 0.0447 0.6237 0.6932
-3.750 -0.3931 0.04886 0.04170 0.0103 1.0005 0.3813
-3.500 -0.3786 0.04594 0.03895 0.0092 1.0005 0.3782
-3.250 -0.2735 0.04133 0.03330 -0.0090 0.6796 0.3809
-3.000 -0.2533 0.03969 0.03083 -0.0098 0.6155 0.3826
-2.750 -0.2295 0.03840 0.02911 -0.0102 0.5797 0.3843
-2.500 -0.2034 0.03733 0.02773 -0.0105 0.5553 0.3863
-2.250 -0.1764 0.03647 0.02668 -0.0109 0.5364 0.3905
-2.000 -0.1486 0.03551 0.02545 -0.0118 0.5207 0.3953
-1.750 -0.1199 0.03457 0.02422 -0.0130 0.5069 0.3990
-1.500 -0.0920 0.03399 0.02356 -0.0131 0.4950 0.4024
-1.250 -0.0630 0.03347 0.02297 -0.0136 0.4849 0.4062
-1.000 -0.0338 0.03307 0.02242 -0.0143 0.4762 0.4114
-0.750 -0.0056 0.03280 0.02208 -0.0144 0.4674 0.4174
-0.500 0.0225 0.03268 0.02199 -0.0147 0.4588 0.4241
-0.250 0.0514 0.03260 0.02170 -0.0150 0.4512 0.4304
0.000 0.0796 0.03267 0.02195 -0.0153 0.4451 0.4362
0.250 0.1084 0.03283 0.02206 -0.0157 0.4391 0.4435
0.500 0.1357 0.03310 0.02238 -0.0155 0.4333 0.4520
0.750 0.1630 0.03350 0.02291 -0.0159 0.4266 0.4622
1.000 0.1896 0.03388 0.02330 -0.0155 0.4208 0.4728
1.250 0.2160 0.03456 0.02417 -0.0156 0.4167 0.4838
1.500 0.2424 0.03538 0.02523 -0.0161 0.4125 0.4963
1.750 0.2682 0.03611 0.02610 -0.0160 0.4074 0.5123
2.000 0.2928 0.03692 0.02707 -0.0156 0.4025 0.5339
2.250 0.3146 0.03815 0.02876 -0.0159 0.3983 0.5599
2.500 0.3351 0.03944 0.03055 -0.0159 0.3961 0.5992
2.750 0.3497 0.04039 0.03229 -0.0141 0.3936 0.6786
3.000 0.4156 0.04196 0.03436 -0.0197 0.3865 0.9995
3.250 0.4262 0.04471 0.03708 -0.0203 0.3846 0.9995
3.500 0.4374 0.04771 0.04007 -0.0210 0.3855 0.9995
3.750 0.4481 0.05093 0.04329 -0.0218 0.3867 0.9995
4.000 0.4583 0.05427 0.04662 -0.0228 0.3877 0.9995
4.250 0.2777 0.07521 0.06861 -0.0564 0.6369 0.9995
4.500 0.2816 0.07650 0.06967 -0.0545 0.6106 0.9995
4.750 0.3091 0.07947 0.07243 -0.0547 0.5917 0.9995
5.000 0.3211 0.08180 0.07460 -0.0538 0.5722 0.9995
5.250 0.3306 0.08366 0.07633 -0.0525 0.5495 0.9995
5.500 0.3548 0.08649 0.07903 -0.0521 0.5303 0.9995
5.750 0.3798 0.08966 0.08209 -0.0517 0.5131 0.9995
6.000 0.3929 0.09222 0.08458 -0.0511 0.4975 0.9995
6.250 0.4015 0.09454 0.08681 -0.0504 0.4824 0.9995
6.750 0.4110 0.09896 0.09108 -0.0493 0.4539 0.9995
7.000 0.4173 0.10141 0.09346 -0.0489 0.4402 0.9995
7.250 0.4256 0.10400 0.09598 -0.0485 0.4269 0.9995
7.500 0.4382 0.10696 0.09888 -0.0483 0.4152 0.9995
7.750 0.4640 0.11057 0.10245 -0.0480 0.4048 0.9995
8.000 0.4551 0.11225 0.10408 -0.0481 0.3934 0.9995
8.250 0.4735 0.11612 0.10789 -0.0481 0.3867 0.9995
|
Polar data table (+)
Polar graphs
<< Back to CAP 21 (TraCFoil) (cap21c-il)