CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 50,000 Max Cl/Cd: 14.64 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cap21c-il-50000-n5.txt Download as CSV file: xf-cap21c-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5617 0.10858 0.09970 0.0118 1.0005 0.1661
-9.750 -0.5702 0.10327 0.09437 0.0084 1.0005 0.1686
-9.500 -0.5864 0.09694 0.08802 0.0035 1.0005 0.1713
-9.250 -0.6074 0.08957 0.08067 -0.0022 1.0005 0.1741
-9.000 -0.5943 0.08707 0.07821 -0.0010 1.0005 0.1764
-8.750 -0.5745 0.08623 0.07743 0.0009 1.0005 0.1793
-8.500 -0.5512 0.08589 0.07715 0.0030 1.0005 0.1827
-8.250 -0.5341 0.08470 0.07602 0.0040 1.0005 0.1868
-8.000 -0.5259 0.08229 0.07364 0.0035 1.0005 0.1910
-7.750 -0.5261 0.07863 0.07001 0.0017 1.0005 0.1946
-7.500 -0.5352 0.07365 0.06506 -0.0016 1.0005 0.1976
-7.250 -0.5493 0.06758 0.05894 -0.0063 1.0005 0.2012
-7.000 -0.5607 0.06183 0.05306 -0.0100 1.0005 0.2051
-6.750 -0.5663 0.05701 0.04807 -0.0124 1.0005 0.2090
-6.500 -0.5645 0.05348 0.04433 -0.0135 1.0005 0.2129
-6.250 -0.5555 0.05144 0.04206 -0.0137 1.0005 0.2169
-6.000 -0.5481 0.04842 0.03894 -0.0136 1.0005 0.2207
-5.750 -0.5358 0.04565 0.03620 -0.0128 1.0005 0.2247
-5.500 -0.5199 0.04391 0.03451 -0.0118 1.0005 0.2278
-5.250 -0.5038 0.04227 0.03288 -0.0109 1.0005 0.2304
-5.000 -0.4872 0.04073 0.03134 -0.0100 1.0005 0.2330
-4.750 -0.4702 0.03927 0.02987 -0.0091 1.0005 0.2357
-4.500 -0.4526 0.03787 0.02847 -0.0083 1.0005 0.2385
-4.250 -0.4343 0.03653 0.02713 -0.0075 1.0005 0.2414
-4.000 -0.3817 0.03494 0.02546 -0.0130 0.9368 0.2466
-3.750 -0.3205 0.03401 0.02365 -0.0179 0.6332 0.2548
-3.500 -0.3022 0.03393 0.02256 -0.0160 0.4955 0.2593
-3.250 -0.2802 0.03346 0.02152 -0.0153 0.4474 0.2630
-3.000 -0.2560 0.03284 0.02051 -0.0150 0.4221 0.2657
-2.750 -0.2307 0.03225 0.01960 -0.0147 0.4058 0.2681
-2.500 -0.2049 0.03178 0.01883 -0.0145 0.3933 0.2704
-2.250 -0.1779 0.03135 0.01818 -0.0143 0.3829 0.2724
-2.000 -0.1507 0.03101 0.01761 -0.0141 0.3738 0.2741
-1.750 -0.1239 0.03031 0.01678 -0.0139 0.3667 0.2773
-1.500 -0.0960 0.02980 0.01625 -0.0138 0.3602 0.2807
-1.250 -0.0677 0.02946 0.01594 -0.0136 0.3538 0.2841
-1.000 -0.0391 0.02924 0.01571 -0.0135 0.3477 0.2878
-0.750 -0.0102 0.02914 0.01559 -0.0134 0.3423 0.2929
-0.500 0.0187 0.02914 0.01553 -0.0133 0.3374 0.2993
-0.250 0.0478 0.02926 0.01551 -0.0132 0.3325 0.3059
0.000 0.0768 0.02923 0.01551 -0.0132 0.3271 0.3117
0.250 0.1058 0.02926 0.01552 -0.0131 0.3205 0.3162
0.500 0.1342 0.02924 0.01556 -0.0129 0.3139 0.3202
0.750 0.1623 0.02930 0.01569 -0.0126 0.3085 0.3251
1.000 0.1904 0.02949 0.01592 -0.0124 0.3044 0.3309
1.250 0.2182 0.02975 0.01619 -0.0121 0.3006 0.3375
1.500 0.2458 0.03015 0.01657 -0.0118 0.2970 0.3447
1.750 0.2725 0.03069 0.01718 -0.0115 0.2934 0.3521
2.000 0.2986 0.03136 0.01798 -0.0112 0.2905 0.3613
2.250 0.3250 0.03176 0.01858 -0.0109 0.2884 0.3727
2.500 0.3503 0.03220 0.01931 -0.0105 0.2860 0.3869
2.750 0.3750 0.03272 0.02016 -0.0101 0.2832 0.4067
3.000 0.3984 0.03318 0.02107 -0.0095 0.2795 0.4392
3.250 0.4189 0.03343 0.02200 -0.0084 0.2748 0.5164
3.500 0.4396 0.03325 0.02311 -0.0059 0.2692 0.7875
3.750 0.4916 0.03423 0.02427 -0.0104 0.2616 0.9995
4.000 0.5121 0.03537 0.02537 -0.0096 0.2578 0.9995
4.250 0.5323 0.03656 0.02654 -0.0088 0.2543 0.9995
4.500 0.5523 0.03779 0.02775 -0.0080 0.2510 0.9995
4.750 0.5719 0.03907 0.02900 -0.0072 0.2479 0.9995
5.000 0.5914 0.04044 0.03034 -0.0064 0.2448 0.9995
5.250 0.6103 0.04200 0.03186 -0.0057 0.2417 0.9995
5.500 0.6264 0.04426 0.03408 -0.0049 0.2378 0.9995
5.750 0.6367 0.04722 0.03718 -0.0045 0.2338 0.9995
6.000 0.6506 0.04864 0.03876 -0.0040 0.2303 0.9995
6.250 0.6594 0.05083 0.04115 -0.0039 0.2255 0.9995
6.500 0.6625 0.05403 0.04454 -0.0042 0.2208 0.9995
6.750 0.6588 0.05822 0.04891 -0.0052 0.2165 0.9995
7.000 0.6490 0.06319 0.05403 -0.0071 0.2122 0.9995
7.250 0.6349 0.06868 0.05962 -0.0098 0.2082 0.9995
7.500 0.6211 0.07441 0.06538 -0.0134 0.2046 0.9995
7.750 0.6181 0.07880 0.06975 -0.0158 0.2015 0.9995
8.000 0.6210 0.08231 0.07324 -0.0170 0.1990 0.9995
8.250 0.6320 0.08456 0.07545 -0.0169 0.1963 0.9995
8.500 0.6475 0.08599 0.07683 -0.0160 0.1935 0.9995
8.750 0.6667 0.08681 0.07758 -0.0142 0.1907 0.9995
9.000 0.6845 0.08815 0.07885 -0.0120 0.1879 0.9995
9.250 0.6443 0.09797 0.08871 -0.0206 0.1822 0.9995
9.500 0.6295 0.10420 0.09496 -0.0246 0.1790 0.9995
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Polar data table (+)
Polar graphs
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