Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il) Reynolds number: 100,000 Max Cl/Cd: 54.44 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-apex16-il-100000-n5.txt Download as CSV file: xf-apex16-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4362 0.10044 0.09570 -0.0433 1.0000 0.0526
-9.000 -0.4495 0.09724 0.09257 -0.0435 1.0000 0.0529
-8.750 -0.4718 0.09368 0.08910 -0.0447 1.0000 0.0533
-8.500 -0.4814 0.08823 0.08358 -0.0525 0.9938 0.0536
-8.250 -0.4943 0.08400 0.07913 -0.0590 0.9843 0.0541
-8.000 -0.4972 0.08059 0.07537 -0.0630 0.9763 0.0545
-7.500 -0.4718 0.07012 0.06508 -0.0648 0.9693 0.0570
-7.250 -0.4616 0.06645 0.06130 -0.0662 0.9643 0.0587
-7.000 -0.4521 0.06298 0.05764 -0.0675 0.9584 0.0605
-6.750 -0.4479 0.06235 0.05622 -0.0677 0.9493 0.0659
-6.500 -0.4305 0.05753 0.05131 -0.0691 0.9457 0.0667
-6.250 -0.4151 0.05362 0.04737 -0.0694 0.9413 0.0678
-6.000 -0.3895 0.04904 0.04227 -0.0680 0.9362 0.0392
-5.750 -0.3672 0.04562 0.03861 -0.0690 0.9327 0.0374
-5.500 -0.3509 0.04302 0.03571 -0.0681 0.9267 0.0361
-5.250 -0.3286 0.04040 0.03276 -0.0679 0.9220 0.0350
-5.000 -0.2999 0.03814 0.03014 -0.0687 0.9189 0.0362
-4.750 -0.2807 0.03641 0.02812 -0.0674 0.9131 0.0370
-4.500 -0.2557 0.03449 0.02590 -0.0671 0.9086 0.0370
-4.250 -0.2256 0.03247 0.02358 -0.0677 0.9057 0.0363
-4.000 -0.1925 0.03062 0.02142 -0.0686 0.9036 0.0359
-3.750 -0.1760 0.02944 0.02006 -0.0664 0.8965 0.0357
-3.500 -0.1463 0.02803 0.01844 -0.0667 0.8931 0.0358
-3.250 -0.1135 0.02671 0.01697 -0.0674 0.8907 0.0361
-3.000 -0.0857 0.02564 0.01580 -0.0673 0.8870 0.0367
-2.750 -0.0649 0.02499 0.01505 -0.0660 0.8808 0.0388
-2.500 -0.0344 0.02431 0.01428 -0.0664 0.8775 0.0408
-2.250 -0.0041 0.02322 0.01326 -0.0669 0.8752 0.0420
-2.000 0.0103 0.02270 0.01272 -0.0646 0.8676 0.0431
-1.750 0.0374 0.02206 0.01199 -0.0647 0.8635 0.0450
-1.500 0.0699 0.02147 0.01124 -0.0658 0.8609 0.0478
-1.250 0.0884 0.02125 0.01089 -0.0643 0.8536 0.0511
-1.000 0.1178 0.02085 0.01040 -0.0647 0.8493 0.0592
-0.750 0.1514 0.02029 0.00986 -0.0659 0.8467 0.0872
-0.500 0.1636 0.01877 0.00986 -0.0639 0.8396 0.5152
-0.250 0.1843 0.01845 0.01013 -0.0618 0.8349 0.6546
0.000 0.2113 0.01828 0.01020 -0.0607 0.8320 0.7278
0.250 0.2299 0.01839 0.01026 -0.0589 0.8238 0.7422
0.500 0.2621 0.01826 0.01007 -0.0597 0.8199 0.7569
0.750 0.2986 0.01805 0.00983 -0.0612 0.8173 0.7722
1.000 0.3153 0.01817 0.00997 -0.0591 0.8084 0.7885
1.250 0.3495 0.01798 0.00978 -0.0601 0.8047 0.8057
1.750 0.4028 0.01786 0.00970 -0.0594 0.7920 0.8460
2.000 0.4419 0.01759 0.00946 -0.0614 0.7887 0.8661
2.250 0.4653 0.01763 0.00958 -0.0606 0.7798 0.8910
2.500 0.5117 0.01740 0.00942 -0.0642 0.7755 0.9147
2.750 0.5587 0.01731 0.00941 -0.0682 0.7691 0.9439
3.000 0.6068 0.01721 0.00939 -0.0726 0.7623 1.0000
3.250 0.6334 0.01717 0.00934 -0.0725 0.7541 1.0000
3.500 0.6627 0.01710 0.00927 -0.0729 0.7460 1.0000
3.750 0.6845 0.01718 0.00937 -0.0719 0.7359 1.0000
4.000 0.7205 0.01699 0.00923 -0.0733 0.7285 1.0000
4.250 0.7414 0.01708 0.00937 -0.0720 0.7168 1.0000
4.500 0.7642 0.01714 0.00947 -0.0711 0.7049 1.0000
4.750 0.7895 0.01713 0.00951 -0.0705 0.6921 1.0000
5.000 0.8150 0.01706 0.00952 -0.0698 0.6765 1.0000
5.250 0.8433 0.01689 0.00936 -0.0695 0.6571 1.0000
5.500 0.8644 0.01694 0.00943 -0.0681 0.6356 1.0000
5.750 0.8901 0.01696 0.00947 -0.0674 0.6149 1.0000
6.000 0.9131 0.01709 0.00966 -0.0664 0.5936 1.0000
6.250 0.9355 0.01727 0.00986 -0.0652 0.5706 1.0000
6.500 0.9543 0.01753 0.01014 -0.0635 0.5447 1.0000
6.750 0.9704 0.01783 0.01039 -0.0612 0.5113 1.0000
7.000 0.9813 0.01827 0.01063 -0.0579 0.4647 1.0000
7.250 0.9862 0.01898 0.01104 -0.0538 0.4055 1.0000
7.500 0.9874 0.01998 0.01162 -0.0494 0.3411 1.0000
7.750 0.9882 0.02115 0.01239 -0.0453 0.2780 1.0000
8.000 0.9919 0.02234 0.01326 -0.0419 0.2248 1.0000
8.250 0.9985 0.02349 0.01420 -0.0391 0.1835 1.0000
8.500 1.0061 0.02467 0.01520 -0.0365 0.1481 1.0000
8.750 1.0133 0.02594 0.01631 -0.0341 0.1137 1.0000
9.000 1.0197 0.02734 0.01754 -0.0315 0.0821 1.0000
9.250 1.0256 0.02882 0.01892 -0.0291 0.0628 1.0000
9.500 1.0320 0.03028 0.02032 -0.0267 0.0530 1.0000
9.750 1.0397 0.03165 0.02177 -0.0246 0.0472 1.0000
10.000 1.0444 0.03326 0.02342 -0.0223 0.0440 1.0000
10.250 1.0512 0.03478 0.02507 -0.0202 0.0415 1.0000
10.500 1.0582 0.03633 0.02677 -0.0183 0.0396 1.0000
10.750 1.0652 0.03793 0.02847 -0.0166 0.0374 1.0000
11.000 1.0707 0.03971 0.03031 -0.0149 0.0351 1.0000
11.250 1.0766 0.04166 0.03231 -0.0132 0.0332 1.0000
11.500 1.0872 0.04335 0.03423 -0.0119 0.0318 1.0000
11.750 1.0987 0.04515 0.03619 -0.0107 0.0305 1.0000
12.000 1.1097 0.04700 0.03820 -0.0095 0.0291 1.0000
12.250 1.1188 0.04895 0.04026 -0.0085 0.0276 1.0000
12.500 1.1262 0.05113 0.04248 -0.0075 0.0261 1.0000
12.750 1.1360 0.05371 0.04521 -0.0066 0.0249 1.0000
13.000 1.1431 0.05627 0.04807 -0.0055 0.0242 1.0000
13.250 1.1470 0.05914 0.05124 -0.0044 0.0236 1.0000
13.500 1.1469 0.06234 0.05473 -0.0034 0.0231 1.0000
13.750 1.1430 0.06578 0.05845 -0.0026 0.0226 1.0000
14.000 1.1358 0.06946 0.06241 -0.0021 0.0221 1.0000
14.250 1.1265 0.07348 0.06669 -0.0019 0.0218 1.0000
14.500 1.1153 0.07770 0.07115 -0.0022 0.0213 1.0000
14.750 1.1035 0.08213 0.07578 -0.0029 0.0208 1.0000
15.000 1.0886 0.08739 0.08128 -0.0043 0.0207 1.0000
15.250 1.0694 0.09366 0.08782 -0.0065 0.0209 1.0000
15.500 1.0529 0.09978 0.09413 -0.0093 0.0206 1.0000
15.750 1.0331 0.10699 0.10155 -0.0131 0.0205 1.0000
16.000 1.0008 0.11775 0.11259 -0.0195 0.0211 1.0000
16.250 0.9639 0.13124 0.12630 -0.0281 0.0221 1.0000
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Polar data table (+)
Polar graphs
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