CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 100,000 Max Cl/Cd: 26 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cap21c-il-100000-n5.txt Download as CSV file: xf-cap21c-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6551 0.10093 0.09449 0.0106 1.0005 0.1183
-10.750 -0.6537 0.09723 0.09080 0.0090 1.0005 0.1212
-10.500 -0.9111 0.04967 0.04266 -0.0287 1.0005 0.1394
-10.250 -0.8885 0.04974 0.04281 -0.0276 1.0005 0.1414
-10.000 -0.8607 0.05056 0.04372 -0.0262 1.0005 0.1431
-9.750 -0.8370 0.05090 0.04411 -0.0251 1.0005 0.1449
-9.500 -0.8191 0.05037 0.04359 -0.0244 1.0005 0.1469
-9.250 -0.8070 0.04886 0.04203 -0.0243 1.0005 0.1495
-9.000 -0.7988 0.04660 0.03967 -0.0244 1.0005 0.1525
-8.750 -0.7909 0.04412 0.03705 -0.0245 1.0005 0.1559
-8.500 -0.7818 0.04165 0.03439 -0.0244 1.0005 0.1596
-8.250 -0.7700 0.03950 0.03205 -0.0241 1.0005 0.1635
-8.000 -0.7547 0.03793 0.03032 -0.0235 1.0005 0.1672
-7.750 -0.7369 0.03680 0.02899 -0.0228 1.0005 0.1702
-7.500 -0.7175 0.03595 0.02801 -0.0220 1.0005 0.1722
-7.250 -0.6994 0.03475 0.02671 -0.0212 1.0005 0.1740
-7.000 -0.6855 0.03237 0.02424 -0.0202 1.0005 0.1775
-6.750 -0.6655 0.03140 0.02329 -0.0192 1.0005 0.1799
-6.500 -0.6444 0.03073 0.02265 -0.0181 1.0005 0.1820
-6.250 -0.6232 0.03014 0.02208 -0.0170 1.0005 0.1842
-6.000 -0.6020 0.02955 0.02151 -0.0159 1.0005 0.1864
-5.750 -0.5806 0.02906 0.02105 -0.0147 1.0005 0.1891
-5.500 -0.5591 0.02859 0.02057 -0.0136 1.0005 0.1921
-5.250 -0.5104 0.02798 0.01993 -0.0177 0.9757 0.1966
-5.000 -0.4647 0.02716 0.01898 -0.0210 0.8924 0.2005
-4.750 -0.4279 0.02697 0.01775 -0.0213 0.5921 0.2035
-4.500 -0.4072 0.02699 0.01698 -0.0200 0.4374 0.2058
-4.250 -0.3823 0.02664 0.01626 -0.0195 0.3896 0.2081
-4.000 -0.3561 0.02626 0.01562 -0.0192 0.3653 0.2104
-3.750 -0.3295 0.02586 0.01502 -0.0189 0.3501 0.2125
-3.500 -0.3029 0.02560 0.01456 -0.0185 0.3384 0.2144
-3.250 -0.2759 0.02548 0.01429 -0.0181 0.3302 0.2163
-3.000 -0.2485 0.02538 0.01412 -0.0177 0.3237 0.2179
-2.750 -0.2222 0.02463 0.01325 -0.0174 0.3177 0.2210
-2.500 -0.1960 0.02374 0.01224 -0.0172 0.3122 0.2249
-2.250 -0.1692 0.02325 0.01165 -0.0168 0.3069 0.2279
-2.000 -0.1421 0.02293 0.01123 -0.0164 0.3019 0.2306
-1.750 -0.1149 0.02276 0.01097 -0.0160 0.2970 0.2332
-1.500 -0.0876 0.02274 0.01085 -0.0157 0.2917 0.2358
-1.250 -0.0598 0.02255 0.01064 -0.0153 0.2889 0.2384
-1.000 -0.0319 0.02236 0.01047 -0.0150 0.2856 0.2410
-0.750 -0.0039 0.02222 0.01033 -0.0147 0.2816 0.2438
-0.500 0.0240 0.02212 0.01023 -0.0143 0.2775 0.2467
-0.250 0.0519 0.02208 0.01019 -0.0140 0.2739 0.2497
0.000 0.0799 0.02207 0.01019 -0.0136 0.2705 0.2529
0.250 0.1078 0.02210 0.01022 -0.0133 0.2671 0.2563
0.500 0.1357 0.02218 0.01030 -0.0130 0.2638 0.2605
0.750 0.1635 0.02230 0.01042 -0.0126 0.2607 0.2649
1.000 0.1913 0.02246 0.01057 -0.0122 0.2577 0.2688
1.250 0.2190 0.02264 0.01075 -0.0119 0.2547 0.2719
1.500 0.2466 0.02285 0.01097 -0.0115 0.2519 0.2742
1.750 0.2735 0.02292 0.01114 -0.0110 0.2491 0.2795
2.000 0.3003 0.02314 0.01143 -0.0106 0.2462 0.2851
2.250 0.3269 0.02354 0.01190 -0.0102 0.2426 0.2909
2.500 0.3528 0.02438 0.01284 -0.0098 0.2374 0.2970
2.750 0.3789 0.02495 0.01352 -0.0094 0.2341 0.3038
3.000 0.4060 0.02503 0.01368 -0.0089 0.2325 0.3115
3.500 0.4593 0.02546 0.01444 -0.0081 0.2286 0.3351
3.750 0.4853 0.02574 0.01494 -0.0076 0.2262 0.3567
4.000 0.5108 0.02600 0.01551 -0.0072 0.2236 0.4002
4.250 0.5340 0.02602 0.01616 -0.0064 0.2209 0.5256
4.500 0.5505 0.02573 0.01683 -0.0033 0.2180 0.7716
4.750 0.5959 0.02607 0.01748 -0.0058 0.2134 0.9758
5.000 0.6272 0.02651 0.01791 -0.0065 0.2093 0.9995
5.250 0.6510 0.02691 0.01831 -0.0056 0.2058 0.9995
5.500 0.6748 0.02732 0.01868 -0.0048 0.2026 0.9995
5.750 0.6986 0.02780 0.01913 -0.0040 0.1999 0.9995
6.000 0.7223 0.02829 0.01958 -0.0032 0.1974 0.9995
6.250 0.7458 0.02882 0.02008 -0.0024 0.1950 0.9995
6.500 0.7686 0.02956 0.02078 -0.0017 0.1923 0.9995
6.750 0.7884 0.03106 0.02230 -0.0009 0.1888 0.9995
7.000 0.8070 0.03260 0.02394 -0.0001 0.1863 0.9995
7.250 0.8282 0.03344 0.02489 0.0007 0.1848 0.9995
7.500 0.8482 0.03443 0.02606 0.0015 0.1827 0.9995
7.750 0.8670 0.03554 0.02732 0.0022 0.1798 0.9995
8.000 0.8848 0.03674 0.02866 0.0030 0.1763 0.9995
8.250 0.9021 0.03794 0.02998 0.0037 0.1725 0.9995
8.500 0.9193 0.03908 0.03122 0.0045 0.1688 0.9995
8.750 0.9360 0.04022 0.03244 0.0052 0.1657 0.9995
9.000 0.9523 0.04138 0.03367 0.0060 0.1630 0.9995
9.250 0.9693 0.04234 0.03468 0.0068 0.1606 0.9995
9.500 0.9871 0.04311 0.03547 0.0076 0.1585 0.9995
9.750 1.0056 0.04375 0.03610 0.0085 0.1565 0.9995
10.000 1.0234 0.04441 0.03681 0.0094 0.1547 0.9995
10.250 1.0386 0.04535 0.03775 0.0103 0.1528 0.9995
10.500 1.0480 0.04709 0.03950 0.0112 0.1505 0.9995
10.750 1.0143 0.05276 0.04542 0.0115 0.1484 0.9995
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Polar data table (+)
Polar graphs
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