CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.38 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cap21c-il-1000000.txt Download as CSV file: xf-cap21c-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.4041 0.08186 0.07844 -0.0067 1.0005 0.0574
-17.750 -1.5597 0.05595 0.05211 -0.0230 1.0005 0.0557
-17.500 -1.6455 0.03692 0.03261 -0.0387 1.0005 0.0554
-17.250 -1.6641 0.03134 0.02685 -0.0426 1.0005 0.0564
-17.000 -1.6704 0.02829 0.02369 -0.0432 1.0005 0.0578
-16.750 -1.6683 0.02638 0.02170 -0.0425 1.0005 0.0591
-16.500 -1.6613 0.02498 0.02024 -0.0414 1.0005 0.0605
-16.250 -1.6502 0.02391 0.01913 -0.0402 1.0005 0.0617
-16.000 -1.6344 0.02301 0.01818 -0.0393 1.0005 0.0628
-15.750 -1.6161 0.02225 0.01736 -0.0386 1.0005 0.0640
-15.500 -1.5959 0.02161 0.01667 -0.0379 1.0005 0.0650
-15.250 -1.5744 0.02107 0.01607 -0.0372 1.0005 0.0657
-15.000 -1.5553 0.02025 0.01521 -0.0365 1.0005 0.0674
-14.750 -1.5363 0.01936 0.01430 -0.0357 1.0005 0.0702
-14.500 -1.5151 0.01866 0.01359 -0.0351 1.0005 0.0723
-14.250 -1.4925 0.01808 0.01299 -0.0345 1.0005 0.0743
-14.000 -1.4689 0.01761 0.01247 -0.0339 1.0005 0.0760
-13.750 -1.4444 0.01721 0.01203 -0.0334 1.0005 0.0772
-13.500 -1.4214 0.01662 0.01141 -0.0328 1.0005 0.0799
-13.250 -1.3982 0.01601 0.01082 -0.0322 1.0005 0.0832
-13.000 -1.3740 0.01553 0.01034 -0.0316 1.0005 0.0860
-12.750 -1.3488 0.01516 0.00994 -0.0311 1.0005 0.0882
-12.500 -1.3232 0.01483 0.00958 -0.0306 1.0005 0.0900
-12.250 -1.2991 0.01430 0.00905 -0.0301 1.0005 0.0943
-12.000 -1.2739 0.01390 0.00867 -0.0295 1.0005 0.0976
-11.750 -1.2481 0.01359 0.00834 -0.0290 1.0005 0.1003
-11.500 -1.2219 0.01333 0.00806 -0.0285 1.0005 0.1021
-11.250 -1.1970 0.01291 0.00766 -0.0279 1.0005 0.1065
-11.000 -1.1714 0.01259 0.00736 -0.0273 1.0005 0.1101
-10.750 -1.1453 0.01234 0.00712 -0.0267 1.0005 0.1131
-10.500 -1.1194 0.01210 0.00685 -0.0261 1.0005 0.1161
-10.250 -1.0941 0.01180 0.00659 -0.0254 1.0005 0.1202
-10.000 -1.0683 0.01159 0.00640 -0.0247 1.0005 0.1235
-9.750 -1.0425 0.01142 0.00621 -0.0240 1.0005 0.1260
-9.500 -1.0165 0.01128 0.00605 -0.0233 1.0005 0.1275
-9.250 -0.9917 0.01100 0.00580 -0.0225 1.0005 0.1314
-9.000 -0.9662 0.01083 0.00566 -0.0217 1.0005 0.1348
-8.750 -0.9405 0.01069 0.00552 -0.0209 1.0005 0.1374
-8.500 -0.9148 0.01056 0.00539 -0.0201 1.0005 0.1393
-8.250 -0.8891 0.01046 0.00527 -0.0192 1.0005 0.1406
-8.000 -0.8642 0.01023 0.00505 -0.0184 1.0005 0.1434
-7.750 -0.8329 0.01005 0.00491 -0.0187 0.9994 0.1462
-7.500 -0.7893 0.00992 0.00480 -0.0215 0.9949 0.1489
-7.250 -0.7444 0.00980 0.00469 -0.0246 0.9899 0.1513
-7.000 -0.7030 0.00971 0.00458 -0.0268 0.9746 0.1532
-6.750 -0.6668 0.00968 0.00449 -0.0278 0.9313 0.1544
-6.500 -0.6449 0.00977 0.00418 -0.0259 0.7911 0.1576
-6.250 -0.6237 0.01041 0.00407 -0.0243 0.5437 0.1599
-6.000 -0.5977 0.01079 0.00398 -0.0238 0.3831 0.1617
-5.500 -0.5410 0.01094 0.00384 -0.0233 0.3045 0.1654
-5.250 -0.5121 0.01093 0.00376 -0.0230 0.2917 0.1668
-5.000 -0.4832 0.01093 0.00370 -0.0228 0.2828 0.1678
-4.750 -0.4541 0.01092 0.00364 -0.0226 0.2765 0.1685
-4.500 -0.4258 0.01070 0.00341 -0.0223 0.2712 0.1713
-4.250 -0.3971 0.01064 0.00333 -0.0221 0.2653 0.1737
-4.000 -0.3680 0.01059 0.00328 -0.0219 0.2617 0.1756
-3.750 -0.3388 0.01056 0.00324 -0.0217 0.2579 0.1773
-3.500 -0.3097 0.01055 0.00320 -0.0214 0.2541 0.1791
-3.250 -0.2807 0.01057 0.00318 -0.0212 0.2497 0.1807
-3.000 -0.2515 0.01055 0.00314 -0.0210 0.2472 0.1818
-2.750 -0.2222 0.01053 0.00310 -0.0208 0.2449 0.1826
-2.500 -0.1933 0.01041 0.00298 -0.0205 0.2423 0.1846
-2.250 -0.1643 0.01032 0.00289 -0.0203 0.2395 0.1870
-2.000 -0.1352 0.01031 0.00286 -0.0201 0.2363 0.1889
-1.750 -0.1062 0.01034 0.00288 -0.0199 0.2329 0.1907
-1.500 -0.0768 0.01032 0.00287 -0.0197 0.2314 0.1926
-1.250 -0.0475 0.01031 0.00286 -0.0195 0.2295 0.1944
-1.000 -0.0181 0.01032 0.00285 -0.0193 0.2274 0.1960
-0.750 0.0112 0.01034 0.00286 -0.0191 0.2252 0.1971
-0.500 0.0403 0.01030 0.00280 -0.0189 0.2230 0.1991
-0.250 0.0693 0.01028 0.00278 -0.0187 0.2199 0.2018
0.000 0.0984 0.01030 0.00281 -0.0185 0.2175 0.2041
0.250 0.1278 0.01027 0.00280 -0.0183 0.2160 0.2062
0.500 0.1572 0.01027 0.00281 -0.0181 0.2143 0.2083
0.750 0.1866 0.01028 0.00282 -0.0179 0.2124 0.2101
1.000 0.2160 0.01030 0.00283 -0.0177 0.2104 0.2118
1.250 0.2453 0.01031 0.00283 -0.0176 0.2080 0.2135
1.500 0.2743 0.01033 0.00284 -0.0174 0.2046 0.2173
1.750 0.3035 0.01036 0.00289 -0.0172 0.2023 0.2203
2.000 0.3330 0.01036 0.00292 -0.0170 0.2010 0.2231
2.250 0.3624 0.01039 0.00296 -0.0169 0.1993 0.2258
2.500 0.3917 0.01043 0.00300 -0.0167 0.1973 0.2279
2.750 0.4211 0.01042 0.00301 -0.0165 0.1954 0.2328
3.000 0.4504 0.01045 0.00306 -0.0164 0.1931 0.2367
3.250 0.4792 0.01057 0.00316 -0.0162 0.1899 0.2404
3.500 0.5084 0.01064 0.00324 -0.0160 0.1879 0.2433
3.750 0.5379 0.01063 0.00328 -0.0159 0.1866 0.2494
4.000 0.5673 0.01064 0.00334 -0.0157 0.1848 0.2556
4.250 0.5967 0.01066 0.00339 -0.0156 0.1826 0.2630
4.500 0.6261 0.01067 0.00344 -0.0155 0.1801 0.2732
4.750 0.6553 0.01071 0.00353 -0.0154 0.1774 0.2915
5.250 0.7153 0.01045 0.00380 -0.0158 0.1731 0.4691
5.500 0.7483 0.01000 0.00395 -0.0168 0.1713 0.6710
5.750 0.7788 0.00969 0.00412 -0.0170 0.1691 0.8278
6.000 0.7933 0.00962 0.00425 -0.0135 0.1671 0.9017
6.250 0.7995 0.00965 0.00435 -0.0082 0.1653 0.9414
6.500 0.8116 0.00976 0.00447 -0.0043 0.1628 0.9648
6.750 0.8320 0.00995 0.00464 -0.0022 0.1602 0.9812
7.000 0.8608 0.01001 0.00472 -0.0020 0.1583 0.9954
7.250 0.9062 0.01007 0.00476 -0.0052 0.1548 0.9995
7.500 0.9325 0.01022 0.00488 -0.0045 0.1515 0.9995
7.750 0.9586 0.01045 0.00507 -0.0039 0.1480 0.9995
8.000 0.9855 0.01062 0.00525 -0.0034 0.1458 0.9995
8.250 1.0130 0.01076 0.00541 -0.0030 0.1437 0.9995
8.500 1.0403 0.01094 0.00557 -0.0026 0.1408 0.9995
8.750 1.0674 0.01115 0.00575 -0.0022 0.1373 0.9995
9.000 1.0941 0.01144 0.00601 -0.0018 0.1332 0.9995
9.250 1.1219 0.01160 0.00619 -0.0015 0.1312 0.9995
9.500 1.1493 0.01182 0.00640 -0.0011 0.1284 0.9995
9.750 1.1763 0.01208 0.00665 -0.0008 0.1253 0.9995
10.000 1.2028 0.01242 0.00697 -0.0004 0.1215 0.9995
10.250 1.2298 0.01268 0.00724 0.0000 0.1194 0.9995
10.500 1.2571 0.01291 0.00749 0.0003 0.1175 0.9995
10.750 1.2839 0.01319 0.00777 0.0006 0.1151 0.9995
11.000 1.3102 0.01352 0.00808 0.0010 0.1124 0.9995
11.250 1.3358 0.01394 0.00850 0.0014 0.1090 0.9995
11.500 1.3618 0.01429 0.00887 0.0019 0.1069 0.9995
11.750 1.3884 0.01456 0.00917 0.0022 0.1055 0.9995
12.000 1.4144 0.01488 0.00950 0.0026 0.1035 0.9995
12.250 1.4399 0.01525 0.00988 0.0030 0.1012 0.9995
12.500 1.4644 0.01572 0.01034 0.0035 0.0984 0.9995
12.750 1.4875 0.01631 0.01093 0.0041 0.0953 0.9995
13.000 1.5128 0.01665 0.01132 0.0046 0.0943 0.9995
13.250 1.5381 0.01698 0.01169 0.0050 0.0932 0.9995
13.500 1.5627 0.01736 0.01211 0.0055 0.0917 0.9995
13.750 1.5864 0.01781 0.01257 0.0061 0.0901 0.9995
14.000 1.6093 0.01832 0.01310 0.0067 0.0882 0.9995
14.250 1.6308 0.01893 0.01373 0.0074 0.0861 0.9995
14.500 1.6495 0.01974 0.01456 0.0084 0.0833 0.9995
14.750 1.6712 0.02026 0.01513 0.0091 0.0823 0.9995
15.000 1.6932 0.02072 0.01565 0.0098 0.0815 0.9995
15.250 1.7140 0.02125 0.01622 0.0106 0.0804 0.9995
15.500 1.7332 0.02186 0.01688 0.0116 0.0791 0.9995
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Polar data table (+)
Polar graphs
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