CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 500,000 Max Cl/Cd: 77.56 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cap21c-il-500000-n5.txt Download as CSV file: xf-cap21c-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.1958 0.09804 0.09426 0.0047 1.0005 0.0615
-16.750 -1.2107 0.09225 0.08839 0.0016 1.0005 0.0623
-16.500 -1.5292 0.03881 0.03395 -0.0378 1.0005 0.0608
-16.250 -1.5406 0.03403 0.02899 -0.0412 1.0005 0.0614
-16.000 -1.5418 0.03134 0.02617 -0.0420 1.0005 0.0621
-15.750 -1.5379 0.02950 0.02421 -0.0415 1.0005 0.0628
-15.500 -1.5300 0.02811 0.02273 -0.0406 1.0005 0.0635
-15.250 -1.5186 0.02701 0.02153 -0.0395 1.0005 0.0641
-15.000 -1.5033 0.02605 0.02048 -0.0386 1.0005 0.0646
-14.750 -1.4865 0.02515 0.01950 -0.0379 1.0005 0.0653
-14.500 -1.4706 0.02409 0.01838 -0.0370 1.0005 0.0676
-14.250 -1.4529 0.02313 0.01738 -0.0363 1.0005 0.0701
-14.000 -1.4340 0.02223 0.01643 -0.0356 1.0005 0.0726
-13.750 -1.4139 0.02142 0.01561 -0.0349 1.0005 0.0752
-13.500 -1.3926 0.02072 0.01489 -0.0343 1.0005 0.0777
-13.250 -1.3702 0.02010 0.01425 -0.0337 1.0005 0.0801
-13.000 -1.3469 0.01956 0.01365 -0.0331 1.0005 0.0820
-12.750 -1.3231 0.01906 0.01310 -0.0326 1.0005 0.0833
-12.500 -1.2987 0.01860 0.01259 -0.0320 1.0005 0.0843
-12.250 -1.2749 0.01808 0.01203 -0.0315 1.0005 0.0869
-12.000 -1.2510 0.01754 0.01148 -0.0309 1.0005 0.0910
-11.750 -1.2268 0.01704 0.01100 -0.0303 1.0005 0.0947
-11.500 -1.2022 0.01660 0.01055 -0.0298 1.0005 0.0982
-11.250 -1.1772 0.01620 0.01017 -0.0293 1.0005 0.1013
-11.000 -1.1518 0.01585 0.00980 -0.0287 1.0005 0.1040
-10.750 -1.1263 0.01553 0.00945 -0.0281 1.0005 0.1062
-10.500 -1.1007 0.01522 0.00911 -0.0275 1.0005 0.1078
-10.250 -1.0754 0.01491 0.00877 -0.0269 1.0005 0.1096
-10.000 -1.0505 0.01457 0.00844 -0.0262 1.0005 0.1144
-9.750 -1.0256 0.01430 0.00822 -0.0254 1.0005 0.1188
-9.500 -1.0007 0.01408 0.00805 -0.0246 1.0005 0.1228
-9.250 -0.9759 0.01389 0.00788 -0.0238 1.0005 0.1268
-9.000 -0.9511 0.01372 0.00773 -0.0229 1.0005 0.1302
-8.750 -0.9263 0.01354 0.00756 -0.0220 1.0005 0.1327
-8.500 -0.9015 0.01336 0.00737 -0.0211 1.0005 0.1343
-8.250 -0.8651 0.01317 0.00716 -0.0225 0.9953 0.1357
-8.000 -0.8233 0.01299 0.00695 -0.0250 0.9854 0.1367
-7.750 -0.7852 0.01286 0.00680 -0.0266 0.9749 0.1375
-7.500 -0.7571 0.01254 0.00645 -0.0263 0.9569 0.1405
-7.250 -0.7247 0.01227 0.00613 -0.0267 0.9076 0.1445
-7.000 -0.7071 0.01266 0.00583 -0.0236 0.6942 0.1471
-6.750 -0.6848 0.01346 0.00567 -0.0227 0.3825 0.1495
-6.500 -0.6570 0.01349 0.00556 -0.0224 0.3302 0.1520
-6.000 -0.6004 0.01344 0.00543 -0.0218 0.2903 0.1576
-5.750 -0.5719 0.01337 0.00534 -0.0216 0.2838 0.1599
-5.500 -0.5434 0.01328 0.00520 -0.0213 0.2773 0.1619
-5.250 -0.5148 0.01321 0.00508 -0.0210 0.2710 0.1638
-5.000 -0.4863 0.01315 0.00497 -0.0207 0.2650 0.1655
-4.750 -0.4577 0.01309 0.00487 -0.0204 0.2589 0.1670
-4.500 -0.4290 0.01307 0.00480 -0.0201 0.2526 0.1686
-4.250 -0.4002 0.01307 0.00478 -0.0199 0.2472 0.1699
-4.000 -0.3714 0.01308 0.00476 -0.0196 0.2429 0.1709
-3.750 -0.3428 0.01306 0.00472 -0.0193 0.2394 0.1716
-3.500 -0.3141 0.01305 0.00469 -0.0190 0.2364 0.1721
-3.250 -0.2854 0.01302 0.00464 -0.0187 0.2348 0.1725
-3.000 -0.2566 0.01295 0.00456 -0.0185 0.2344 0.1729
-2.750 -0.2278 0.01289 0.00448 -0.0182 0.2338 0.1731
-2.500 -0.1990 0.01284 0.00442 -0.0179 0.2331 0.1734
-2.250 -0.1706 0.01265 0.00420 -0.0176 0.2324 0.1751
-2.000 -0.1423 0.01243 0.00395 -0.0173 0.2314 0.1782
-1.750 -0.1138 0.01228 0.00380 -0.0170 0.2302 0.1807
-1.500 -0.0853 0.01217 0.00368 -0.0167 0.2287 0.1826
-1.250 -0.0566 0.01209 0.00358 -0.0164 0.2269 0.1846
-1.000 -0.0279 0.01202 0.00351 -0.0161 0.2247 0.1866
-0.750 0.0007 0.01197 0.00347 -0.0158 0.2223 0.1887
-0.500 0.0294 0.01194 0.00344 -0.0155 0.2196 0.1909
-0.250 0.0581 0.01192 0.00343 -0.0152 0.2168 0.1932
0.000 0.0868 0.01191 0.00342 -0.0149 0.2140 0.1956
0.250 0.1154 0.01192 0.00343 -0.0146 0.2112 0.1982
0.500 0.1440 0.01194 0.00344 -0.0143 0.2086 0.2009
0.750 0.1727 0.01197 0.00346 -0.0140 0.2059 0.2035
1.000 0.2013 0.01201 0.00350 -0.0137 0.2034 0.2062
1.250 0.2298 0.01208 0.00356 -0.0134 0.2004 0.2087
1.500 0.2583 0.01217 0.00365 -0.0131 0.1965 0.2109
1.750 0.2866 0.01230 0.00378 -0.0128 0.1930 0.2128
2.000 0.3149 0.01246 0.00396 -0.0124 0.1905 0.2143
2.250 0.3430 0.01267 0.00419 -0.0121 0.1881 0.2155
2.500 0.3715 0.01280 0.00433 -0.0118 0.1870 0.2166
2.750 0.4003 0.01282 0.00436 -0.0115 0.1867 0.2174
3.000 0.4292 0.01283 0.00438 -0.0113 0.1861 0.2181
3.250 0.4580 0.01286 0.00444 -0.0110 0.1855 0.2185
3.500 0.4866 0.01289 0.00448 -0.0107 0.1848 0.2205
3.750 0.5152 0.01292 0.00452 -0.0104 0.1840 0.2239
4.000 0.5438 0.01295 0.00457 -0.0102 0.1829 0.2280
4.250 0.5723 0.01299 0.00464 -0.0099 0.1816 0.2331
4.500 0.6009 0.01305 0.00473 -0.0096 0.1800 0.2397
4.750 0.6293 0.01310 0.00483 -0.0093 0.1782 0.2466
5.000 0.6577 0.01317 0.00495 -0.0090 0.1760 0.2533
5.250 0.6860 0.01324 0.00505 -0.0087 0.1735 0.2603
5.500 0.7143 0.01332 0.00516 -0.0084 0.1709 0.2678
6.000 0.7704 0.01343 0.00531 -0.0079 0.1640 0.3070
6.250 0.7981 0.01341 0.00542 -0.0076 0.1599 0.3680
6.500 0.8237 0.01284 0.00565 -0.0073 0.1559 0.6481
6.750 0.8372 0.01236 0.00596 -0.0036 0.1526 0.9032
7.000 0.8663 0.01260 0.00628 -0.0033 0.1491 0.9817
7.250 0.9035 0.01276 0.00646 -0.0049 0.1485 0.9995
7.500 0.9302 0.01294 0.00665 -0.0043 0.1477 0.9995
7.750 0.9569 0.01313 0.00685 -0.0038 0.1467 0.9995
8.000 0.9837 0.01332 0.00706 -0.0033 0.1453 0.9995
8.250 1.0104 0.01353 0.00727 -0.0028 0.1435 0.9995
8.500 1.0371 0.01374 0.00747 -0.0023 0.1409 0.9995
8.750 1.0637 0.01395 0.00765 -0.0018 0.1374 0.9995
9.000 1.0900 0.01419 0.00786 -0.0014 0.1332 0.9995
9.250 1.1161 0.01445 0.00806 -0.0009 0.1289 0.9995
9.500 1.1418 0.01477 0.00833 -0.0003 0.1239 0.9995
9.750 1.1671 0.01514 0.00870 0.0002 0.1184 0.9995
10.000 1.1932 0.01543 0.00902 0.0007 0.1170 0.9995
10.250 1.2192 0.01573 0.00934 0.0012 0.1158 0.9995
10.500 1.2449 0.01605 0.00969 0.0017 0.1143 0.9995
10.750 1.2703 0.01638 0.01005 0.0022 0.1124 0.9995
11.000 1.2954 0.01675 0.01045 0.0028 0.1103 0.9995
11.250 1.3202 0.01714 0.01084 0.0033 0.1079 0.9995
11.500 1.3444 0.01756 0.01126 0.0039 0.1054 0.9995
11.750 1.3682 0.01802 0.01171 0.0045 0.1029 0.9995
12.000 1.3915 0.01851 0.01220 0.0052 0.1001 0.9995
12.250 1.4143 0.01904 0.01274 0.0059 0.0972 0.9995
12.500 1.4364 0.01961 0.01335 0.0067 0.0943 0.9995
12.750 1.4576 0.02023 0.01401 0.0075 0.0919 0.9995
13.000 1.4803 0.02069 0.01453 0.0082 0.0915 0.9995
13.250 1.5026 0.02118 0.01511 0.0090 0.0909 0.9995
13.500 1.5242 0.02169 0.01569 0.0098 0.0902 0.9995
13.750 1.5450 0.02224 0.01630 0.0106 0.0893 0.9995
14.000 1.5649 0.02284 0.01696 0.0115 0.0882 0.9995
14.250 1.5837 0.02349 0.01767 0.0125 0.0869 0.9995
14.500 1.6010 0.02420 0.01843 0.0136 0.0855 0.9995
14.750 1.6155 0.02497 0.01926 0.0150 0.0841 0.9995
15.000 1.6278 0.02587 0.02020 0.0165 0.0826 0.9995
15.250 1.6382 0.02689 0.02127 0.0180 0.0811 0.9995
15.500 1.6460 0.02812 0.02255 0.0194 0.0797 0.9995
15.750 1.6510 0.02963 0.02412 0.0206 0.0782 0.9995
16.000 1.6530 0.03155 0.02611 0.0213 0.0768 0.9995
16.250 1.6511 0.03409 0.02875 0.0214 0.0753 0.9995
16.500 1.6428 0.03778 0.03261 0.0201 0.0739 0.9995
16.750 1.6230 0.04394 0.03897 0.0161 0.0728 0.9995
17.000 1.5575 0.05859 0.05396 0.0054 0.0721 0.9995
17.250 1.3027 0.09928 0.09532 -0.0189 0.0722 0.9995
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