CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 500,000 Max Cl/Cd: 74 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cap21c-il-500000.txt Download as CSV file: xf-cap21c-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.3122 0.08628 0.08246 -0.0047 1.0005 0.0716
-17.250 -1.3540 0.07680 0.07285 -0.0103 1.0005 0.0726
-17.000 -1.4029 0.06619 0.06208 -0.0169 1.0005 0.0733
-16.750 -1.4506 0.05520 0.05089 -0.0242 1.0005 0.0739
-16.500 -1.4837 0.04567 0.04113 -0.0316 1.0005 0.0746
-16.250 -1.4987 0.03921 0.03447 -0.0371 1.0005 0.0754
-16.000 -1.5031 0.03513 0.03022 -0.0401 1.0005 0.0763
-15.750 -1.5011 0.03242 0.02736 -0.0414 1.0005 0.0770
-15.500 -1.4987 0.03016 0.02498 -0.0417 1.0005 0.0781
-15.250 -1.5002 0.02794 0.02270 -0.0410 1.0005 0.0801
-15.000 -1.4944 0.02644 0.02116 -0.0398 1.0005 0.0819
-14.750 -1.4820 0.02533 0.02001 -0.0388 1.0005 0.0838
-14.500 -1.4654 0.02441 0.01903 -0.0381 1.0005 0.0858
-14.250 -1.4466 0.02362 0.01815 -0.0373 1.0005 0.0877
-14.000 -1.4260 0.02296 0.01738 -0.0367 1.0005 0.0892
-13.750 -1.4093 0.02192 0.01633 -0.0358 1.0005 0.0922
-13.500 -1.3896 0.02112 0.01553 -0.0351 1.0005 0.0950
-13.250 -1.3678 0.02050 0.01488 -0.0344 1.0005 0.0977
-13.000 -1.3446 0.01999 0.01429 -0.0338 1.0005 0.1003
-12.750 -1.3213 0.01947 0.01370 -0.0332 1.0005 0.1026
-12.500 -1.2998 0.01877 0.01302 -0.0325 1.0005 0.1063
-12.250 -1.2760 0.01831 0.01256 -0.0320 1.0005 0.1095
-12.000 -1.2511 0.01794 0.01215 -0.0314 1.0005 0.1126
-11.750 -1.2262 0.01757 0.01171 -0.0309 1.0005 0.1154
-11.500 -1.2023 0.01712 0.01132 -0.0303 1.0005 0.1193
-11.250 -1.1769 0.01683 0.01103 -0.0297 1.0005 0.1225
-11.000 -1.1511 0.01658 0.01073 -0.0292 1.0005 0.1255
-10.750 -1.1251 0.01635 0.01039 -0.0287 1.0005 0.1277
-10.500 -1.1008 0.01592 0.01002 -0.0280 1.0005 0.1313
-10.250 -1.0750 0.01573 0.00985 -0.0274 1.0005 0.1342
-10.000 -1.0488 0.01559 0.00969 -0.0268 1.0005 0.1372
-9.750 -1.0226 0.01546 0.00950 -0.0262 1.0005 0.1398
-9.500 -0.9976 0.01515 0.00916 -0.0255 1.0005 0.1424
-9.250 -0.9726 0.01490 0.00896 -0.0247 1.0005 0.1450
-9.000 -0.9471 0.01477 0.00884 -0.0240 1.0005 0.1474
-8.750 -0.9216 0.01465 0.00869 -0.0232 1.0005 0.1498
-8.500 -0.8963 0.01451 0.00852 -0.0223 1.0005 0.1521
-8.250 -0.8710 0.01440 0.00835 -0.0215 1.0005 0.1539
-8.000 -0.8467 0.01402 0.00798 -0.0206 1.0005 0.1564
-7.750 -0.8219 0.01385 0.00786 -0.0197 1.0005 0.1588
-7.500 -0.7968 0.01377 0.00781 -0.0188 1.0005 0.1610
-7.250 -0.7717 0.01369 0.00773 -0.0179 1.0005 0.1633
-7.000 -0.7468 0.01359 0.00760 -0.0170 1.0005 0.1656
-6.750 -0.7218 0.01354 0.00751 -0.0161 1.0005 0.1675
-6.500 -0.6881 0.01322 0.00719 -0.0170 0.9981 0.1698
-6.250 -0.6357 0.01295 0.00700 -0.0216 0.9887 0.1729
-6.000 -0.5888 0.01285 0.00693 -0.0249 0.9669 0.1755
-5.750 -0.5451 0.01274 0.00668 -0.0272 0.8796 0.1779
-5.500 -0.5292 0.01361 0.00645 -0.0240 0.5659 0.1795
-5.250 -0.5050 0.01414 0.00631 -0.0232 0.3791 0.1811
-5.000 -0.4772 0.01428 0.00621 -0.0229 0.3386 0.1825
-4.750 -0.4498 0.01400 0.00586 -0.0226 0.3207 0.1849
-4.500 -0.4217 0.01392 0.00573 -0.0223 0.3093 0.1869
-4.250 -0.3933 0.01386 0.00566 -0.0220 0.3010 0.1888
-4.000 -0.3650 0.01387 0.00560 -0.0217 0.2943 0.1909
-3.750 -0.3363 0.01383 0.00553 -0.0214 0.2888 0.1930
-3.500 -0.3078 0.01380 0.00543 -0.0211 0.2834 0.1949
-3.250 -0.2793 0.01381 0.00536 -0.0208 0.2782 0.1964
-3.000 -0.2505 0.01378 0.00529 -0.0205 0.2741 0.1975
-2.750 -0.2226 0.01345 0.00497 -0.0202 0.2704 0.1999
-2.500 -0.1944 0.01337 0.00488 -0.0199 0.2665 0.2018
-2.250 -0.1660 0.01338 0.00487 -0.0195 0.2631 0.2038
-2.000 -0.1372 0.01335 0.00485 -0.0193 0.2604 0.2062
-1.750 -0.1084 0.01333 0.00481 -0.0190 0.2574 0.2084
-1.500 -0.0797 0.01331 0.00476 -0.0187 0.2543 0.2103
-1.250 -0.0511 0.01338 0.00476 -0.0184 0.2510 0.2120
-1.000 -0.0230 0.01334 0.00469 -0.0181 0.2479 0.2143
-0.750 0.0056 0.01319 0.00460 -0.0178 0.2457 0.2167
-0.500 0.0343 0.01314 0.00458 -0.0176 0.2433 0.2189
-0.250 0.0631 0.01313 0.00457 -0.0173 0.2407 0.2211
0.000 0.0918 0.01314 0.00456 -0.0170 0.2383 0.2234
0.250 0.1204 0.01321 0.00459 -0.0167 0.2355 0.2257
0.500 0.1488 0.01338 0.00471 -0.0164 0.2327 0.2276
0.750 0.1776 0.01323 0.00463 -0.0162 0.2307 0.2305
1.000 0.2064 0.01318 0.00463 -0.0159 0.2284 0.2335
1.250 0.2352 0.01319 0.00466 -0.0157 0.2261 0.2364
1.500 0.2640 0.01322 0.00470 -0.0154 0.2239 0.2396
1.750 0.2929 0.01330 0.00474 -0.0152 0.2215 0.2428
2.000 0.3209 0.01348 0.00490 -0.0149 0.2181 0.2469
2.250 0.3500 0.01338 0.00489 -0.0147 0.2163 0.2509
2.500 0.3790 0.01337 0.00492 -0.0145 0.2139 0.2550
2.750 0.4080 0.01342 0.00497 -0.0143 0.2116 0.2588
3.000 0.4369 0.01338 0.00501 -0.0141 0.2094 0.2647
3.250 0.4657 0.01342 0.00507 -0.0139 0.2073 0.2709
3.500 0.4943 0.01353 0.00519 -0.0137 0.2050 0.2783
3.750 0.5228 0.01373 0.00542 -0.0135 0.2026 0.2877
4.000 0.5520 0.01365 0.00547 -0.0134 0.2005 0.3012
4.250 0.5811 0.01358 0.00555 -0.0133 0.1981 0.3271
4.500 0.6107 0.01332 0.00566 -0.0135 0.1957 0.4281
4.750 0.6417 0.01256 0.00583 -0.0142 0.1935 0.7140
5.000 0.6533 0.01227 0.00602 -0.0099 0.1917 0.8715
5.250 0.6577 0.01239 0.00621 -0.0041 0.1896 0.9363
5.500 0.6778 0.01255 0.00640 -0.0018 0.1875 0.9719
5.750 0.7099 0.01261 0.00649 -0.0021 0.1851 0.9932
6.000 0.7586 0.01265 0.00652 -0.0060 0.1819 0.9995
6.250 0.7837 0.01277 0.00663 -0.0051 0.1796 0.9995
6.500 0.8090 0.01292 0.00674 -0.0043 0.1774 0.9995
6.750 0.8337 0.01331 0.00707 -0.0035 0.1743 0.9995
7.000 0.8602 0.01341 0.00721 -0.0028 0.1725 0.9995
7.250 0.8867 0.01354 0.00737 -0.0022 0.1701 0.9995
7.500 0.9135 0.01367 0.00751 -0.0017 0.1675 0.9995
7.750 0.9403 0.01379 0.00759 -0.0012 0.1647 0.9995
8.000 0.9663 0.01409 0.00783 -0.0007 0.1610 0.9995
8.250 0.9934 0.01424 0.00803 -0.0002 0.1585 0.9995
8.500 1.0205 0.01439 0.00822 0.0002 0.1556 0.9995
8.750 1.0475 0.01458 0.00841 0.0006 0.1529 0.9995
9.000 1.0740 0.01482 0.00862 0.0010 0.1500 0.9995
9.250 1.0992 0.01527 0.00901 0.0016 0.1466 0.9995
9.500 1.1263 0.01547 0.00929 0.0020 0.1445 0.9995
9.750 1.1531 0.01569 0.00956 0.0023 0.1417 0.9995
10.000 1.1795 0.01594 0.00981 0.0028 0.1387 0.9995
10.250 1.2049 0.01629 0.01012 0.0032 0.1355 0.9995
10.500 1.2299 0.01673 0.01057 0.0038 0.1326 0.9995
10.750 1.2560 0.01703 0.01093 0.0042 0.1305 0.9995
11.000 1.2817 0.01735 0.01130 0.0046 0.1280 0.9995
11.250 1.3068 0.01773 0.01168 0.0051 0.1253 0.9995
11.500 1.3306 0.01821 0.01216 0.0057 0.1226 0.9995
11.750 1.3531 0.01885 0.01280 0.0064 0.1199 0.9995
12.000 1.3779 0.01923 0.01326 0.0069 0.1182 0.9995
12.250 1.4020 0.01965 0.01375 0.0075 0.1160 0.9995
12.500 1.4253 0.02012 0.01425 0.0081 0.1138 0.9995
12.750 1.4473 0.02068 0.01482 0.0088 0.1115 0.9995
13.000 1.4667 0.02144 0.01557 0.0097 0.1090 0.9995
13.250 1.4860 0.02221 0.01640 0.0106 0.1069 0.9995
13.500 1.5076 0.02274 0.01702 0.0113 0.1053 0.9995
13.750 1.5279 0.02333 0.01768 0.0121 0.1035 0.9995
14.000 1.5468 0.02399 0.01840 0.0130 0.1015 0.9995
14.250 1.5630 0.02478 0.01922 0.0141 0.0997 0.9995
14.500 1.5743 0.02575 0.02021 0.0157 0.0979 0.9995
14.750 1.5798 0.02713 0.02162 0.0175 0.0957 0.9995
15.000 1.5877 0.02842 0.02301 0.0189 0.0944 0.9995
15.250 1.5979 0.02961 0.02432 0.0198 0.0935 0.9995
15.500 1.6052 0.03111 0.02595 0.0204 0.0924 0.9995
15.750 1.6098 0.03300 0.02795 0.0207 0.0912 0.9995
16.000 1.6111 0.03544 0.03051 0.0202 0.0901 0.9995
16.250 1.6083 0.03874 0.03394 0.0186 0.0889 0.9995
16.500 1.5988 0.04348 0.03881 0.0155 0.0879 0.9995
16.750 1.5789 0.05030 0.04579 0.0105 0.0869 0.9995
17.000 1.5468 0.05894 0.05459 0.0046 0.0859 0.9995
17.250 1.5095 0.06770 0.06348 -0.0005 0.0848 0.9995
17.500 1.4797 0.07475 0.07059 -0.0039 0.0833 0.9995
17.750 1.4470 0.08253 0.07851 -0.0081 0.0825 0.9995
18.000 1.4061 0.09192 0.08808 -0.0135 0.0819 0.9995
18.250 1.3643 0.10199 0.09833 -0.0193 0.0811 0.9995
18.500 1.3119 0.11409 0.11061 -0.0264 0.0799 0.9995
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