Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 200,000 Max Cl/Cd: 76.81 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-apex16-il-200000-n5.txt Download as CSV file: xf-apex16-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3835 0.09055 0.08695 -0.0682 0.9878 0.0279
-9.250 -0.3831 0.08551 0.08185 -0.0739 0.9836 0.0279
-8.750 -0.3903 0.07724 0.07341 -0.0818 0.9711 0.0279
-7.250 -0.3628 0.05100 0.04618 -0.0896 0.9379 0.0293
-7.000 -0.3464 0.04784 0.04298 -0.0908 0.9346 0.0305
-6.750 -0.3253 0.04503 0.04003 -0.0923 0.9323 0.0319
-6.500 -0.3084 0.04274 0.03738 -0.0899 0.9256 0.0267
-6.250 -0.2924 0.03902 0.03342 -0.0902 0.9216 0.0250
-6.000 -0.2681 0.03578 0.02988 -0.0909 0.9192 0.0238
-5.750 -0.2518 0.03334 0.02716 -0.0893 0.9132 0.0229
-5.500 -0.2291 0.03075 0.02428 -0.0888 0.9086 0.0224
-5.250 -0.2001 0.02821 0.02142 -0.0892 0.9060 0.0222
-5.000 -0.1690 0.02598 0.01890 -0.0900 0.9040 0.0223
-4.750 -0.1522 0.02466 0.01740 -0.0879 0.8970 0.0227
-4.500 -0.1240 0.02342 0.01595 -0.0881 0.8936 0.0243
-4.250 -0.0929 0.02189 0.01423 -0.0887 0.8913 0.0247
-4.000 -0.0603 0.02042 0.01258 -0.0896 0.8895 0.0247
-3.750 -0.0413 0.01948 0.01155 -0.0878 0.8831 0.0248
-3.500 -0.0140 0.01846 0.01044 -0.0877 0.8793 0.0252
-3.250 0.0160 0.01751 0.00940 -0.0882 0.8766 0.0256
-3.000 0.0470 0.01664 0.00848 -0.0890 0.8744 0.0263
-2.750 0.0630 0.01617 0.00797 -0.0867 0.8671 0.0270
-2.500 0.0910 0.01568 0.00743 -0.0869 0.8633 0.0279
-2.250 0.1189 0.01477 0.00647 -0.0873 0.8604 0.0308
-2.000 0.1377 0.01439 0.00605 -0.0857 0.8539 0.0319
-1.750 0.1647 0.01399 0.00557 -0.0857 0.8495 0.0336
-1.500 0.1963 0.01363 0.00508 -0.0866 0.8464 0.0360
-1.250 0.2193 0.01346 0.00482 -0.0857 0.8403 0.0395
-1.000 0.2469 0.01320 0.00454 -0.0858 0.8354 0.0503
-0.750 0.2693 0.01171 0.00420 -0.0857 0.8316 0.4322
-0.500 0.2873 0.01139 0.00430 -0.0838 0.8246 0.5419
-0.250 0.3136 0.01118 0.00433 -0.0834 0.8196 0.6103
0.000 0.3416 0.01108 0.00433 -0.0833 0.8149 0.6505
0.250 0.3655 0.01106 0.00434 -0.0825 0.8079 0.6686
0.500 0.3974 0.01098 0.00422 -0.0833 0.8031 0.6810
0.750 0.4212 0.01098 0.00424 -0.0825 0.7955 0.6930
1.000 0.4509 0.01092 0.00418 -0.0829 0.7895 0.7057
1.250 0.4759 0.01091 0.00420 -0.0823 0.7818 0.7185
1.500 0.5047 0.01086 0.00416 -0.0825 0.7748 0.7315
1.750 0.5290 0.01087 0.00421 -0.0817 0.7664 0.7447
2.000 0.5579 0.01083 0.00420 -0.0819 0.7592 0.7585
2.250 0.5808 0.01085 0.00429 -0.0809 0.7498 0.7729
2.500 0.6081 0.01084 0.00431 -0.0807 0.7415 0.7879
2.750 0.6325 0.01086 0.00440 -0.0799 0.7320 0.8039
3.000 0.6568 0.01088 0.00449 -0.0792 0.7221 0.8209
3.250 0.6831 0.01089 0.00453 -0.0788 0.7124 0.8383
3.500 0.7079 0.01091 0.00460 -0.0782 0.7013 0.8563
3.750 0.7324 0.01094 0.00470 -0.0775 0.6889 0.8754
4.000 0.7598 0.01095 0.00478 -0.0773 0.6743 0.8958
4.250 0.7916 0.01100 0.00483 -0.0781 0.6511 0.9202
4.500 0.8319 0.01112 0.00494 -0.0809 0.6235 0.9534
4.750 0.8640 0.01131 0.00510 -0.0821 0.6025 1.0000
5.250 0.9033 0.01176 0.00546 -0.0791 0.5621 1.0000
5.500 0.9194 0.01206 0.00566 -0.0768 0.5316 1.0000
5.750 0.9312 0.01247 0.00591 -0.0737 0.4897 1.0000
6.000 0.9377 0.01303 0.00620 -0.0697 0.4387 1.0000
6.250 0.9424 0.01364 0.00655 -0.0654 0.3923 1.0000
6.500 0.9464 0.01436 0.00701 -0.0611 0.3426 1.0000
6.750 0.9517 0.01514 0.00753 -0.0573 0.2935 1.0000
7.000 0.9572 0.01603 0.00814 -0.0537 0.2424 1.0000
7.250 0.9646 0.01693 0.00882 -0.0505 0.1962 1.0000
7.500 0.9750 0.01775 0.00947 -0.0480 0.1630 1.0000
8.000 0.9958 0.01951 0.01093 -0.0432 0.1020 1.0000
8.250 1.0041 0.02058 0.01179 -0.0406 0.0667 1.0000
8.500 1.0126 0.02167 0.01273 -0.0381 0.0451 1.0000
8.750 1.0243 0.02259 0.01365 -0.0360 0.0378 1.0000
9.000 1.0349 0.02360 0.01471 -0.0338 0.0338 1.0000
9.250 1.0477 0.02447 0.01568 -0.0320 0.0318 1.0000
9.500 1.0596 0.02541 0.01672 -0.0302 0.0296 1.0000
9.750 1.0698 0.02648 0.01786 -0.0282 0.0274 1.0000
10.000 1.0767 0.02781 0.01925 -0.0260 0.0257 1.0000
10.250 1.0846 0.02910 0.02065 -0.0240 0.0247 1.0000
10.500 1.0939 0.03033 0.02200 -0.0222 0.0238 1.0000
10.750 1.1030 0.03161 0.02338 -0.0205 0.0227 1.0000
11.000 1.1118 0.03294 0.02484 -0.0188 0.0214 1.0000
11.250 1.1200 0.03434 0.02631 -0.0173 0.0201 1.0000
11.500 1.1253 0.03606 0.02809 -0.0156 0.0192 1.0000
11.750 1.1280 0.03821 0.03031 -0.0137 0.0184 1.0000
12.000 1.1374 0.03974 0.03197 -0.0124 0.0179 1.0000
12.250 1.1466 0.04134 0.03372 -0.0112 0.0173 1.0000
12.500 1.1547 0.04302 0.03554 -0.0101 0.0163 1.0000
12.750 1.1617 0.04477 0.03742 -0.0090 0.0153 1.0000
13.000 1.1677 0.04666 0.03942 -0.0080 0.0146 1.0000
13.250 1.1728 0.04873 0.04160 -0.0070 0.0141 1.0000
13.500 1.1768 0.05096 0.04393 -0.0061 0.0137 1.0000
13.750 1.1801 0.05345 0.04653 -0.0052 0.0133 1.0000
14.000 1.1814 0.05649 0.04972 -0.0043 0.0128 1.0000
14.250 1.1822 0.05928 0.05277 -0.0037 0.0127 1.0000
14.500 1.1803 0.06242 0.05615 -0.0032 0.0124 1.0000
14.750 1.1758 0.06595 0.05994 -0.0030 0.0121 1.0000
15.000 1.1699 0.06980 0.06402 -0.0031 0.0120 1.0000
15.250 1.1618 0.07404 0.06849 -0.0035 0.0119 1.0000
15.500 1.1513 0.07875 0.07344 -0.0045 0.0116 1.0000
15.750 1.1385 0.08403 0.07896 -0.0060 0.0114 1.0000
16.000 1.1255 0.08958 0.08473 -0.0080 0.0111 1.0000
16.250 1.1091 0.09604 0.09142 -0.0107 0.0112 1.0000
16.500 1.0926 0.10291 0.09850 -0.0140 0.0112 1.0000
16.750 1.0762 0.11016 0.10594 -0.0180 0.0110 1.0000
17.000 1.0558 0.11871 0.11471 -0.0229 0.0112 1.0000
17.250 1.0343 0.12814 0.12433 -0.0287 0.0112 1.0000
17.500 1.0087 0.13934 0.13570 -0.0356 0.0116 1.0000
17.750 0.9819 0.15189 0.14835 -0.0434 0.0119 1.0000
18.000 0.9410 0.17061 0.16716 -0.0540 0.0123 1.0000
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Polar data table (+)
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