CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 200,000 Max Cl/Cd: 48.11 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cap21c-il-200000-n5.txt Download as CSV file: xf-cap21c-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.2738 0.04655 0.04095 -0.0331 1.0005 0.0905
-14.250 -1.2995 0.03967 0.03384 -0.0389 1.0005 0.0919
-14.000 -1.3046 0.03674 0.03080 -0.0398 1.0005 0.0936
-13.750 -1.3024 0.03484 0.02883 -0.0393 1.0005 0.0954
-13.500 -1.2949 0.03340 0.02730 -0.0384 1.0005 0.0975
-13.250 -1.2827 0.03214 0.02595 -0.0377 1.0005 0.0997
-13.000 -1.2683 0.03097 0.02467 -0.0370 1.0005 0.1020
-12.750 -1.2523 0.02987 0.02345 -0.0363 1.0005 0.1042
-12.500 -1.2347 0.02885 0.02229 -0.0357 1.0005 0.1061
-12.250 -1.2159 0.02791 0.02121 -0.0350 1.0005 0.1078
-12.000 -1.1969 0.02697 0.02019 -0.0343 1.0005 0.1099
-11.750 -1.1768 0.02628 0.01946 -0.0335 1.0005 0.1134
-11.500 -1.1543 0.02591 0.01914 -0.0328 1.0005 0.1166
-11.250 -1.1304 0.02571 0.01898 -0.0322 1.0005 0.1198
-11.000 -1.1061 0.02553 0.01882 -0.0316 1.0005 0.1231
-10.750 -1.0818 0.02527 0.01854 -0.0310 1.0005 0.1263
-10.500 -1.0579 0.02490 0.01811 -0.0303 1.0005 0.1293
-10.250 -1.0342 0.02445 0.01759 -0.0297 1.0005 0.1320
-10.000 -1.0105 0.02396 0.01701 -0.0291 1.0005 0.1341
-9.750 -0.9867 0.02349 0.01646 -0.0284 1.0005 0.1358
-9.500 -0.9626 0.02308 0.01592 -0.0277 1.0005 0.1371
-9.250 -0.9400 0.02237 0.01517 -0.0269 1.0005 0.1396
-9.000 -0.9167 0.02193 0.01478 -0.0261 1.0005 0.1433
-8.750 -0.8919 0.02186 0.01478 -0.0253 1.0005 0.1462
-8.500 -0.8668 0.02184 0.01482 -0.0244 1.0005 0.1487
-8.250 -0.8421 0.02175 0.01476 -0.0236 1.0005 0.1510
-8.000 -0.8180 0.02156 0.01458 -0.0226 1.0005 0.1532
-7.750 -0.7942 0.02131 0.01432 -0.0217 1.0005 0.1555
-7.500 -0.7706 0.02104 0.01401 -0.0206 1.0005 0.1579
-7.250 -0.7470 0.02082 0.01378 -0.0196 1.0005 0.1605
-7.000 -0.7234 0.02061 0.01357 -0.0186 1.0005 0.1631
-6.750 -0.6998 0.02038 0.01332 -0.0176 1.0005 0.1654
-6.500 -0.6590 0.02006 0.01296 -0.0199 0.9892 0.1677
-6.250 -0.6160 0.01969 0.01252 -0.0227 0.9679 0.1695
-6.000 -0.5767 0.01935 0.01211 -0.0245 0.9202 0.1709
-5.750 -0.5410 0.01929 0.01159 -0.0248 0.7528 0.1720
-5.500 -0.5245 0.02023 0.01125 -0.0221 0.4248 0.1726
-5.250 -0.4982 0.02037 0.01109 -0.0217 0.3621 0.1733
-5.000 -0.4734 0.01939 0.00990 -0.0213 0.3344 0.1778
-4.750 -0.4468 0.01895 0.00938 -0.0209 0.3201 0.1812
-4.500 -0.4197 0.01870 0.00905 -0.0206 0.3082 0.1836
-4.250 -0.3925 0.01853 0.00881 -0.0202 0.2975 0.1858
-4.000 -0.3650 0.01839 0.00861 -0.0198 0.2903 0.1878
-3.750 -0.3371 0.01823 0.00841 -0.0194 0.2874 0.1899
-3.500 -0.3093 0.01808 0.00823 -0.0191 0.2842 0.1920
-3.250 -0.2814 0.01793 0.00805 -0.0187 0.2810 0.1942
-3.000 -0.2534 0.01781 0.00790 -0.0184 0.2778 0.1965
-2.750 -0.2254 0.01773 0.00780 -0.0180 0.2744 0.1992
-2.500 -0.1974 0.01766 0.00770 -0.0176 0.2711 0.2019
-2.250 -0.1694 0.01758 0.00757 -0.0173 0.2672 0.2042
-2.000 -0.1415 0.01746 0.00738 -0.0169 0.2627 0.2060
-1.750 -0.1135 0.01737 0.00721 -0.0166 0.2579 0.2076
-1.500 -0.0856 0.01730 0.00708 -0.0162 0.2530 0.2092
-1.250 -0.0576 0.01728 0.00701 -0.0159 0.2486 0.2107
-1.000 -0.0298 0.01731 0.00700 -0.0155 0.2440 0.2121
-0.750 -0.0020 0.01743 0.00709 -0.0151 0.2393 0.2133
-0.500 0.0258 0.01765 0.00729 -0.0148 0.2350 0.2145
-0.250 0.0541 0.01762 0.00724 -0.0144 0.2343 0.2157
0.000 0.0824 0.01760 0.00723 -0.0141 0.2334 0.2166
0.250 0.1107 0.01761 0.00723 -0.0138 0.2325 0.2175
0.500 0.1389 0.01763 0.00727 -0.0134 0.2314 0.2182
0.750 0.1670 0.01756 0.00722 -0.0131 0.2301 0.2203
1.000 0.1947 0.01741 0.00709 -0.0127 0.2287 0.2250
1.250 0.2226 0.01735 0.00707 -0.0123 0.2272 0.2297
1.500 0.2505 0.01736 0.00714 -0.0120 0.2255 0.2353
1.750 0.2784 0.01740 0.00724 -0.0116 0.2235 0.2409
2.000 0.3064 0.01743 0.00733 -0.0113 0.2210 0.2459
2.250 0.3343 0.01747 0.00741 -0.0109 0.2182 0.2502
2.500 0.3622 0.01754 0.00752 -0.0106 0.2155 0.2540
2.750 0.3901 0.01766 0.00768 -0.0102 0.2131 0.2577
3.000 0.4180 0.01778 0.00783 -0.0098 0.2108 0.2614
3.250 0.4458 0.01791 0.00801 -0.0095 0.2084 0.2652
3.500 0.4736 0.01804 0.00815 -0.0091 0.2060 0.2689
3.750 0.5013 0.01814 0.00826 -0.0087 0.2032 0.2725
4.250 0.5560 0.01830 0.00848 -0.0079 0.1967 0.2928
4.500 0.5828 0.01857 0.00881 -0.0075 0.1928 0.3081
4.750 0.6085 0.01921 0.00961 -0.0071 0.1883 0.3340
5.000 0.6346 0.01939 0.01009 -0.0067 0.1867 0.4013
5.250 0.6584 0.01892 0.01038 -0.0059 0.1859 0.6001
5.500 0.6751 0.01847 0.01070 -0.0027 0.1850 0.8268
5.750 0.7151 0.01856 0.01100 -0.0042 0.1835 0.9809
6.000 0.7489 0.01882 0.01128 -0.0051 0.1817 0.9995
6.250 0.7744 0.01911 0.01158 -0.0044 0.1799 0.9995
6.500 0.7998 0.01941 0.01191 -0.0038 0.1778 0.9995
6.750 0.8253 0.01970 0.01221 -0.0031 0.1754 0.9995
7.000 0.8510 0.01992 0.01246 -0.0025 0.1725 0.9995
7.250 0.8769 0.02009 0.01262 -0.0018 0.1695 0.9995
7.500 0.9029 0.02022 0.01273 -0.0012 0.1665 0.9995
7.750 0.9287 0.02037 0.01286 -0.0006 0.1637 0.9995
8.000 0.9543 0.02057 0.01303 0.0000 0.1611 0.9995
8.250 0.9797 0.02078 0.01319 0.0006 0.1585 0.9995
8.500 1.0046 0.02108 0.01345 0.0013 0.1556 0.9995
8.750 1.0282 0.02163 0.01396 0.0020 0.1521 0.9995
9.000 1.0509 0.02244 0.01481 0.0028 0.1489 0.9995
9.250 1.0754 0.02287 0.01535 0.0034 0.1478 0.9995
9.500 1.0997 0.02329 0.01585 0.0040 0.1463 0.9995
9.750 1.1238 0.02370 0.01633 0.0046 0.1442 0.9995
10.000 1.1478 0.02410 0.01679 0.0053 0.1417 0.9995
10.250 1.1715 0.02450 0.01724 0.0059 0.1388 0.9995
10.500 1.1948 0.02492 0.01770 0.0066 0.1361 0.9995
10.750 1.2176 0.02537 0.01818 0.0074 0.1335 0.9995
11.000 1.2399 0.02581 0.01864 0.0081 0.1310 0.9995
11.250 1.2618 0.02623 0.01905 0.0089 0.1284 0.9995
11.500 1.2828 0.02668 0.01953 0.0098 0.1256 0.9995
11.750 1.3020 0.02730 0.02012 0.0108 0.1225 0.9995
12.000 1.3180 0.02830 0.02115 0.0119 0.1188 0.9995
12.250 1.3349 0.02923 0.02216 0.0129 0.1171 0.9995
12.500 1.3516 0.03009 0.02315 0.0139 0.1159 0.9995
12.750 1.3664 0.03108 0.02426 0.0150 0.1145 0.9995
13.000 1.3783 0.03217 0.02548 0.0163 0.1130 0.9995
13.250 1.3871 0.03340 0.02684 0.0178 0.1115 0.9995
13.500 1.3934 0.03483 0.02838 0.0191 0.1100 0.9995
13.750 1.3966 0.03654 0.03022 0.0202 0.1084 0.9995
14.000 1.3963 0.03871 0.03251 0.0207 0.1069 0.9995
14.250 1.3909 0.04166 0.03561 0.0202 0.1055 0.9995
14.500 1.3751 0.04650 0.04064 0.0175 0.1041 0.9995
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