CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 200,000 Max Cl/Cd: 38.36 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cap21c-il-200000.txt Download as CSV file: xf-cap21c-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6712 0.16933 0.16498 0.0407 1.0005 0.1154
-14.250 -1.2198 0.05153 0.04624 -0.0351 1.0005 0.1142
-14.000 -1.2482 0.04528 0.03978 -0.0391 1.0005 0.1158
-13.000 -1.1972 0.04184 0.03636 -0.0373 1.0005 0.1241
-12.750 -1.2160 0.03784 0.03191 -0.0368 1.0005 0.1266
-12.500 -1.2054 0.03616 0.03013 -0.0360 1.0005 0.1290
-12.250 -1.1753 0.03677 0.03093 -0.0353 1.0005 0.1308
-12.000 -1.1481 0.03720 0.03146 -0.0345 1.0005 0.1329
-11.750 -1.1299 0.03658 0.03078 -0.0338 1.0005 0.1355
-11.500 -1.1238 0.03439 0.02825 -0.0331 1.0005 0.1393
-11.250 -1.1079 0.03311 0.02683 -0.0324 1.0005 0.1422
-11.000 -1.0768 0.03392 0.02783 -0.0317 1.0005 0.1440
-10.750 -1.0487 0.03447 0.02848 -0.0310 1.0005 0.1461
-10.500 -1.0265 0.03411 0.02809 -0.0303 1.0005 0.1489
-10.250 -1.0147 0.03218 0.02582 -0.0295 1.0005 0.1529
-10.000 -0.9967 0.03088 0.02437 -0.0288 1.0005 0.1558
-9.750 -0.9690 0.03109 0.02472 -0.0282 1.0005 0.1575
-9.500 -0.9424 0.03126 0.02498 -0.0275 1.0005 0.1595
-9.250 -0.9179 0.03114 0.02485 -0.0267 1.0005 0.1622
-9.000 -0.8997 0.03001 0.02348 -0.0259 1.0005 0.1664
-8.750 -0.8809 0.02882 0.02211 -0.0250 1.0005 0.1698
-8.500 -0.8542 0.02889 0.02232 -0.0243 1.0005 0.1716
-8.250 -0.8287 0.02888 0.02239 -0.0235 1.0005 0.1738
-8.000 -0.8046 0.02863 0.02215 -0.0227 1.0005 0.1764
-7.750 -0.7847 0.02773 0.02106 -0.0217 1.0005 0.1805
-7.500 -0.7657 0.02657 0.01969 -0.0206 1.0005 0.1839
-7.250 -0.7410 0.02629 0.01952 -0.0198 1.0005 0.1859
-7.000 -0.7169 0.02605 0.01935 -0.0188 1.0005 0.1880
-6.750 -0.6934 0.02573 0.01906 -0.0178 1.0005 0.1906
-6.500 -0.6717 0.02512 0.01834 -0.0167 1.0005 0.1943
-6.250 -0.6514 0.02430 0.01724 -0.0156 1.0005 0.1979
-6.000 -0.6285 0.02345 0.01650 -0.0147 1.0005 0.1999
-5.750 -0.6049 0.02304 0.01616 -0.0137 1.0005 0.2020
-5.500 -0.5815 0.02265 0.01580 -0.0127 1.0005 0.2043
-5.250 -0.5584 0.02219 0.01533 -0.0117 1.0005 0.2072
-5.000 -0.5168 0.02165 0.01463 -0.0144 0.9936 0.2116
-4.750 -0.4410 0.02054 0.01351 -0.0233 0.9094 0.2157
-4.500 -0.4124 0.02152 0.01294 -0.0220 0.4611 0.2181
-4.250 -0.3873 0.02159 0.01265 -0.0213 0.4021 0.2207
-4.000 -0.3607 0.02144 0.01224 -0.0209 0.3787 0.2240
-3.750 -0.3336 0.02126 0.01179 -0.0205 0.3641 0.2268
-3.500 -0.3066 0.02083 0.01117 -0.0202 0.3536 0.2291
-3.250 -0.2793 0.02044 0.01075 -0.0198 0.3447 0.2312
-3.000 -0.2517 0.02024 0.01049 -0.0195 0.3375 0.2336
-2.750 -0.2238 0.02007 0.01024 -0.0192 0.3307 0.2362
-2.500 -0.1959 0.02000 0.01003 -0.0189 0.3246 0.2394
-2.250 -0.1675 0.01989 0.00979 -0.0186 0.3186 0.2424
-2.000 -0.1396 0.01957 0.00939 -0.0183 0.3136 0.2449
-1.750 -0.1117 0.01941 0.00921 -0.0180 0.3093 0.2473
-1.500 -0.0833 0.01926 0.00910 -0.0177 0.3049 0.2501
-1.250 -0.0549 0.01921 0.00900 -0.0174 0.3006 0.2535
-1.000 -0.0265 0.01925 0.00890 -0.0172 0.2969 0.2567
-0.750 0.0021 0.01926 0.00884 -0.0169 0.2930 0.2592
-0.500 0.0302 0.01898 0.00867 -0.0166 0.2888 0.2620
-0.250 0.0585 0.01892 0.00863 -0.0163 0.2850 0.2650
0.000 0.0869 0.01898 0.00864 -0.0160 0.2818 0.2683
0.250 0.1153 0.01918 0.00878 -0.0158 0.2788 0.2718
0.500 0.1439 0.01917 0.00881 -0.0155 0.2756 0.2751
0.750 0.1718 0.01908 0.00885 -0.0152 0.2719 0.2790
1.000 0.2000 0.01913 0.00892 -0.0149 0.2683 0.2838
1.250 0.2284 0.01937 0.00907 -0.0146 0.2653 0.2885
1.500 0.2563 0.01951 0.00932 -0.0143 0.2626 0.2930
1.750 0.2843 0.01957 0.00954 -0.0140 0.2595 0.2981
2.000 0.3125 0.01971 0.00972 -0.0136 0.2562 0.3040
2.250 0.3402 0.01974 0.00984 -0.0133 0.2529 0.3102
2.500 0.3682 0.01998 0.01006 -0.0131 0.2500 0.3184
2.750 0.3957 0.02025 0.01048 -0.0128 0.2471 0.3275
3.000 0.4234 0.02035 0.01078 -0.0124 0.2434 0.3390
3.250 0.4512 0.02042 0.01100 -0.0121 0.2399 0.3543
3.500 0.4790 0.02044 0.01119 -0.0119 0.2370 0.3820
3.750 0.5061 0.02027 0.01152 -0.0118 0.2345 0.4976
4.000 0.5106 0.01975 0.01223 -0.0059 0.2326 0.8371
4.250 0.5366 0.01996 0.01274 -0.0039 0.2294 0.9664
4.500 0.5935 0.02030 0.01308 -0.0093 0.2246 0.9995
4.750 0.6171 0.02054 0.01325 -0.0082 0.2218 0.9995
5.000 0.6412 0.02089 0.01346 -0.0073 0.2194 0.9995
5.250 0.6636 0.02154 0.01415 -0.0062 0.2165 0.9995
5.500 0.6858 0.02206 0.01481 -0.0051 0.2130 0.9995
5.750 0.7096 0.02247 0.01523 -0.0041 0.2099 0.9995
6.000 0.7345 0.02271 0.01542 -0.0033 0.2072 0.9995
6.250 0.7604 0.02291 0.01551 -0.0027 0.2048 0.9995
6.500 0.7842 0.02357 0.01620 -0.0019 0.2019 0.9995
6.750 0.8064 0.02417 0.01699 -0.0009 0.1980 0.9995
7.000 0.8310 0.02458 0.01742 -0.0002 0.1949 0.9995
7.250 0.8568 0.02481 0.01762 0.0004 0.1924 0.9995
7.500 0.8834 0.02502 0.01772 0.0009 0.1903 0.9995
7.750 0.9074 0.02584 0.01854 0.0015 0.1878 0.9995
8.000 0.9275 0.02677 0.01974 0.0025 0.1839 0.9995
8.250 0.9517 0.02717 0.02022 0.0031 0.1807 0.9995
8.500 0.9781 0.02718 0.02018 0.0037 0.1781 0.9995
8.750 1.0057 0.02717 0.02003 0.0041 0.1760 0.9995
9.000 1.0291 0.02794 0.02081 0.0047 0.1735 0.9995
9.250 1.0476 0.02893 0.02207 0.0056 0.1696 0.9995
9.500 1.0707 0.02934 0.02255 0.0063 0.1665 0.9995
9.750 1.0968 0.02934 0.02249 0.0069 0.1641 0.9995
10.000 1.1243 0.02931 0.02236 0.0073 0.1622 0.9995
10.250 1.1464 0.03021 0.02326 0.0079 0.1598 0.9995
10.500 1.1603 0.03168 0.02505 0.0091 0.1567 0.9995
10.750 1.1777 0.03272 0.02626 0.0100 0.1538 0.9995
11.000 1.1999 0.03311 0.02666 0.0107 0.1515 0.9995
11.250 1.2268 0.03298 0.02642 0.0112 0.1495 0.9995
11.500 1.2536 0.03315 0.02642 0.0116 0.1474 0.9995
11.750 1.2619 0.03494 0.02850 0.0129 0.1448 0.9995
12.000 1.2687 0.03666 0.03052 0.0142 0.1419 0.9995
12.250 1.2812 0.03774 0.03171 0.0153 0.1395 0.9995
12.500 1.3005 0.03818 0.03214 0.0161 0.1376 0.9995
12.750 1.3247 0.03824 0.03210 0.0169 0.1358 0.9995
13.000 1.3465 0.03890 0.03264 0.0175 0.1339 0.9995
13.250 1.3344 0.04168 0.03571 0.0195 0.1324 0.9995
13.500 1.3017 0.04621 0.04061 0.0203 0.1309 0.9995
13.750 0.7249 0.16405 0.15971 -0.0505 0.1332 0.9995
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