Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 50,000 Max Cl/Cd: 34.02 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-apex16-il-50000.txt Download as CSV file: xf-apex16-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Apex 16 (normalized using XFOIL date021206)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4059 0.13410 0.12693 -0.0396 1.0000 0.1807
-11.000 -0.3967 0.13031 0.12318 -0.0383 1.0000 0.1891
-10.750 -0.4162 0.12924 0.12223 -0.0390 1.0000 0.1963
-10.500 -0.4049 0.12555 0.11857 -0.0372 1.0000 0.2094
-10.250 -0.4015 0.12268 0.11574 -0.0357 1.0000 0.2230
-10.000 -0.4045 0.12044 0.11356 -0.0343 1.0000 0.2383
-9.750 -0.3944 0.11776 0.11091 -0.0316 1.0000 0.2621
-9.500 -0.3890 0.11581 0.10901 -0.0289 1.0000 0.2900
-9.250 -0.3850 0.11418 0.10744 -0.0260 1.0000 0.3209
-9.000 -0.3819 0.11257 0.10588 -0.0230 1.0000 0.3512
-8.750 -0.3748 0.11056 0.10392 -0.0201 1.0000 0.3805
-8.500 -0.3648 0.10818 0.10157 -0.0174 1.0000 0.4092
-8.250 -0.3554 0.10582 0.09923 -0.0148 1.0000 0.4380
-8.000 -0.3464 0.10342 0.09687 -0.0123 1.0000 0.4666
-7.750 -0.3384 0.10108 0.09457 -0.0097 1.0000 0.4969
-7.500 -0.3297 0.09872 0.09226 -0.0072 1.0000 0.5269
-7.250 -0.3213 0.09637 0.08995 -0.0048 1.0000 0.5582
-7.000 -0.3142 0.09378 0.08741 -0.0027 1.0000 0.5838
-6.750 -0.3099 0.09144 0.08512 -0.0006 1.0000 0.6034
-6.500 -0.3114 0.08924 0.08296 0.0015 1.0000 0.6138
-6.250 -0.3150 0.08705 0.08084 0.0033 1.0000 0.6165
-6.000 -0.3227 0.08516 0.07902 0.0057 1.0000 0.6185
-4.750 -0.4816 0.07652 0.07112 0.0220 1.0000 0.5203
-4.250 -0.5501 0.04753 0.04094 -0.0218 1.0000 0.3080
-4.000 -0.5120 0.04194 0.03399 -0.0278 1.0000 0.2488
-3.750 -0.4784 0.04093 0.03185 -0.0283 1.0000 0.2099
-3.500 -0.4509 0.03984 0.03025 -0.0274 1.0000 0.1865
-3.250 -0.4252 0.03898 0.02893 -0.0264 1.0000 0.1718
-3.000 -0.4009 0.03799 0.02760 -0.0252 1.0000 0.1621
-2.750 -0.3766 0.03758 0.02673 -0.0240 1.0000 0.1512
-2.500 -0.3533 0.03638 0.02530 -0.0229 1.0000 0.1431
-2.250 -0.3302 0.03596 0.02454 -0.0215 1.0000 0.1369
-2.000 -0.3081 0.03486 0.02340 -0.0204 1.0000 0.1335
-1.750 -0.2861 0.03411 0.02257 -0.0192 1.0000 0.1308
-1.500 -0.2651 0.03348 0.02190 -0.0179 1.0000 0.1323
-1.250 -0.2446 0.03301 0.02137 -0.0165 1.0000 0.1349
-1.000 -0.2241 0.03266 0.02097 -0.0152 1.0000 0.1367
-0.750 -0.2048 0.03239 0.02062 -0.0138 1.0000 0.1383
-0.500 -0.1849 0.03194 0.02015 -0.0129 1.0000 0.1420
-0.250 -0.1643 0.03167 0.01978 -0.0124 1.0000 0.1503
0.000 -0.1422 0.03138 0.01936 -0.0123 1.0000 0.1646
0.250 -0.1174 0.03097 0.01894 -0.0127 1.0000 0.1913
0.500 -0.1009 0.02969 0.02010 -0.0100 1.0000 0.6775
0.750 -0.0904 0.02888 0.02024 -0.0038 1.0000 1.0000
1.000 -0.0693 0.02941 0.02028 -0.0044 1.0000 1.0000
1.250 -0.0485 0.03002 0.02053 -0.0050 1.0000 1.0000
1.500 -0.0284 0.03069 0.02092 -0.0055 1.0000 1.0000
1.750 -0.0088 0.03142 0.02141 -0.0059 1.0000 1.0000
2.000 0.0103 0.03220 0.02197 -0.0063 1.0000 1.0000
2.250 0.0290 0.03303 0.02262 -0.0065 1.0000 1.0000
2.500 0.0473 0.03390 0.02335 -0.0068 1.0000 1.0000
2.750 0.0651 0.03482 0.02415 -0.0070 1.0000 1.0000
3.000 0.0826 0.03579 0.02501 -0.0072 1.0000 1.0000
3.250 0.1785 0.03976 0.02880 -0.0218 0.9564 1.0000
3.500 0.2141 0.04101 0.03000 -0.0250 0.9373 1.0000
3.750 0.2521 0.04240 0.03136 -0.0284 0.9192 1.0000
4.000 0.2907 0.04379 0.03273 -0.0318 0.9022 1.0000
4.250 0.3307 0.04519 0.03415 -0.0351 0.8855 1.0000
4.500 0.3568 0.04615 0.03514 -0.0363 0.8686 1.0000
4.750 0.3853 0.04721 0.03623 -0.0377 0.8518 1.0000
5.000 0.4155 0.04829 0.03739 -0.0393 0.8349 1.0000
5.250 0.4483 0.04935 0.03853 -0.0411 0.8179 1.0000
5.500 0.4847 0.05036 0.03964 -0.0432 0.8007 1.0000
5.750 0.5237 0.05125 0.04068 -0.0454 0.7837 1.0000
6.000 0.5420 0.05217 0.04171 -0.0450 0.7647 1.0000
6.250 0.5714 0.05295 0.04263 -0.0457 0.7459 1.0000
6.500 0.6128 0.05331 0.04318 -0.0474 0.7270 1.0000
6.750 0.6409 0.05379 0.04386 -0.0475 0.7064 1.0000
7.000 0.6776 0.05371 0.04400 -0.0480 0.6850 1.0000
7.250 0.7183 0.05309 0.04365 -0.0482 0.6627 1.0000
7.500 0.7684 0.05142 0.04234 -0.0485 0.6398 1.0000
7.750 0.8085 0.04991 0.04116 -0.0476 0.6156 1.0000
8.000 0.9184 0.04184 0.03386 -0.0491 0.5942 1.0000
8.250 1.0359 0.03201 0.02466 -0.0505 0.5323 1.0000
8.500 1.0406 0.03059 0.02304 -0.0436 0.4711 1.0000
8.750 1.0397 0.03076 0.02283 -0.0375 0.4049 1.0000
9.000 1.0321 0.03209 0.02360 -0.0316 0.3361 1.0000
9.250 1.0199 0.03433 0.02511 -0.0260 0.2687 1.0000
9.500 1.0121 0.03728 0.02736 -0.0216 0.2043 1.0000
9.750 1.0446 0.04048 0.02993 -0.0214 0.1514 1.0000
10.000 1.1104 0.04426 0.03361 -0.0260 0.1236 1.0000
10.250 1.1560 0.04815 0.03766 -0.0288 0.1109 1.0000
10.500 1.1723 0.05126 0.04128 -0.0272 0.1056 1.0000
10.750 1.1973 0.05518 0.04551 -0.0272 0.1017 1.0000
11.000 1.2136 0.05961 0.05015 -0.0265 0.0985 1.0000
11.250 1.2045 0.06258 0.05361 -0.0222 0.0974 1.0000
11.500 1.1924 0.06565 0.05706 -0.0179 0.0967 1.0000
11.750 1.1770 0.06889 0.06063 -0.0138 0.0962 1.0000
12.000 1.1604 0.07245 0.06448 -0.0103 0.0963 1.0000
12.250 1.1420 0.07626 0.06855 -0.0074 0.0966 1.0000
12.500 1.1220 0.08043 0.07295 -0.0051 0.0971 1.0000
12.750 1.1025 0.08500 0.07772 -0.0037 0.0977 1.0000
13.000 1.0832 0.09000 0.08288 -0.0030 0.0983 1.0000
13.250 1.0700 0.09556 0.08856 -0.0030 0.0990 1.0000
13.500 0.9555 0.10860 0.10192 -0.0106 0.1099 1.0000
13.750 0.9385 0.11638 0.10972 -0.0139 0.1115 1.0000
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Polar data table (+)
Polar graphs
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