DAE-51 AIRFOIL (dae51-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: DAE-51 AIRFOIL (dae51-il) Reynolds number: 200,000 Max Cl/Cd: 84.63 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae51-il-200000-n5.txt Download as CSV file: xf-dae51-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DAE-51 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3707 0.11767 0.11402 -0.0268 1.0000 0.0254
-10.000 -0.3681 0.11414 0.11052 -0.0298 1.0000 0.0256
-9.750 -0.3639 0.11050 0.10691 -0.0324 1.0000 0.0257
-9.500 -0.3599 0.10684 0.10328 -0.0350 1.0000 0.0258
-9.250 -0.3557 0.10320 0.09968 -0.0376 1.0000 0.0259
-9.000 -0.3456 0.09983 0.09633 -0.0348 1.0000 0.0270
-8.750 -0.3378 0.09708 0.09361 -0.0353 1.0000 0.0277
-8.500 -0.3328 0.09409 0.09065 -0.0366 1.0000 0.0282
-8.250 -0.3306 0.09116 0.08778 -0.0377 1.0000 0.0285
-8.000 -0.3222 0.08754 0.08419 -0.0409 0.9902 0.0288
-7.750 -0.3087 0.08327 0.07992 -0.0459 0.9774 0.0291
-7.500 -0.2954 0.07885 0.07550 -0.0513 0.9648 0.0293
-7.250 -0.2822 0.06682 0.06339 -0.0678 0.9489 0.0197
-7.000 -0.2649 0.06261 0.05914 -0.0729 0.9402 0.0193
-6.750 -0.2466 0.05719 0.05364 -0.0798 0.9302 0.0189
-6.500 -0.2266 0.05075 0.04705 -0.0873 0.9207 0.0184
-6.250 -0.2045 0.04343 0.03944 -0.0943 0.9130 0.0180
-6.000 -0.1825 0.03615 0.03170 -0.0993 0.9043 0.0177
-5.750 -0.1586 0.03030 0.02524 -0.1022 0.8983 0.0178
-5.500 -0.1334 0.02623 0.02055 -0.1036 0.8910 0.0189
-5.250 -0.1071 0.02323 0.01692 -0.1042 0.8852 0.0196
-5.000 -0.0804 0.02108 0.01428 -0.1045 0.8793 0.0198
-4.750 -0.0536 0.01935 0.01218 -0.1045 0.8731 0.0201
-4.500 -0.0269 0.01795 0.01057 -0.1045 0.8682 0.0207
-4.250 0.0001 0.01700 0.00947 -0.1045 0.8615 0.0215
-4.000 0.0272 0.01616 0.00849 -0.1043 0.8558 0.0225
-3.750 0.0546 0.01546 0.00765 -0.1042 0.8501 0.0241
-3.500 0.0821 0.01487 0.00694 -0.1040 0.8437 0.0262
-3.250 0.1093 0.01419 0.00621 -0.1039 0.8386 0.0283
-3.000 0.1370 0.01368 0.00566 -0.1039 0.8318 0.0306
-2.750 0.1647 0.01325 0.00514 -0.1038 0.8259 0.0341
-2.500 0.1926 0.01285 0.00470 -0.1038 0.8199 0.0401
-2.250 0.2207 0.01246 0.00428 -0.1038 0.8133 0.0477
-2.000 0.2487 0.01213 0.00394 -0.1038 0.8079 0.0654
-1.750 0.2766 0.01175 0.00371 -0.1040 0.8006 0.1079
-1.500 0.3043 0.01124 0.00353 -0.1042 0.7947 0.2099
-1.250 0.3317 0.01076 0.00349 -0.1044 0.7874 0.3442
-1.000 0.3585 0.01033 0.00344 -0.1043 0.7809 0.4787
-0.750 0.3838 0.00992 0.00346 -0.1037 0.7737 0.6178
-0.500 0.4054 0.00949 0.00345 -0.1018 0.7667 0.7657
-0.250 0.4341 0.00907 0.00327 -0.1012 0.7594 1.0000
0.000 0.4624 0.00912 0.00319 -0.1012 0.7517 1.0000
0.250 0.4906 0.00918 0.00315 -0.1012 0.7436 1.0000
0.500 0.5187 0.00924 0.00309 -0.1011 0.7358 1.0000
0.750 0.5468 0.00932 0.00308 -0.1012 0.7268 1.0000
1.000 0.5748 0.00939 0.00305 -0.1011 0.7185 1.0000
1.250 0.6027 0.00947 0.00307 -0.1010 0.7088 1.0000
1.500 0.6305 0.00955 0.00309 -0.1010 0.6992 1.0000
1.750 0.6583 0.00964 0.00310 -0.1009 0.6896 1.0000
2.000 0.6859 0.00974 0.00315 -0.1008 0.6787 1.0000
2.250 0.7135 0.00985 0.00322 -0.1007 0.6675 1.0000
2.500 0.7410 0.00996 0.00329 -0.1005 0.6560 1.0000
2.750 0.7683 0.01009 0.00336 -0.1004 0.6439 1.0000
3.000 0.7955 0.01023 0.00346 -0.1002 0.6312 1.0000
3.250 0.8225 0.01038 0.00357 -0.1000 0.6178 1.0000
3.500 0.8494 0.01054 0.00370 -0.0998 0.6036 1.0000
3.750 0.8761 0.01072 0.00384 -0.0995 0.5889 1.0000
4.000 0.9026 0.01092 0.00402 -0.0993 0.5736 1.0000
4.250 0.9289 0.01113 0.00420 -0.0990 0.5574 1.0000
4.500 0.9550 0.01136 0.00441 -0.0987 0.5402 1.0000
4.750 0.9809 0.01161 0.00463 -0.0983 0.5221 1.0000
5.000 1.0063 0.01189 0.00489 -0.0979 0.5028 1.0000
5.250 1.0313 0.01220 0.00516 -0.0974 0.4815 1.0000
5.500 1.0557 0.01255 0.00545 -0.0969 0.4577 1.0000
5.750 1.0795 0.01294 0.00580 -0.0963 0.4303 1.0000
6.000 1.1020 0.01342 0.00617 -0.0955 0.3982 1.0000
6.250 1.1239 0.01396 0.00659 -0.0946 0.3625 1.0000
6.500 1.1449 0.01459 0.00707 -0.0937 0.3265 1.0000
6.750 1.1651 0.01529 0.00763 -0.0927 0.2881 1.0000
7.000 1.1838 0.01611 0.00826 -0.0915 0.2465 1.0000
7.250 1.2017 0.01701 0.00895 -0.0903 0.2055 1.0000
7.500 1.2189 0.01795 0.00970 -0.0890 0.1675 1.0000
7.750 1.2360 0.01889 0.01050 -0.0877 0.1341 1.0000
8.000 1.2523 0.01987 0.01135 -0.0863 0.1055 1.0000
8.250 1.2679 0.02088 0.01225 -0.0848 0.0817 1.0000
8.500 1.2823 0.02194 0.01321 -0.0831 0.0637 1.0000
8.750 1.2967 0.02295 0.01420 -0.0814 0.0518 1.0000
9.000 1.3098 0.02397 0.01525 -0.0795 0.0435 1.0000
9.250 1.3215 0.02495 0.01629 -0.0774 0.0379 1.0000
9.500 1.3303 0.02618 0.01753 -0.0751 0.0335 1.0000
9.750 1.3416 0.02725 0.01874 -0.0731 0.0306 1.0000
10.000 1.3511 0.02849 0.02006 -0.0712 0.0281 1.0000
10.250 1.3565 0.03008 0.02171 -0.0690 0.0259 1.0000
10.500 1.3656 0.03143 0.02318 -0.0672 0.0242 1.0000
10.750 1.3734 0.03292 0.02482 -0.0655 0.0227 1.0000
11.000 1.3797 0.03458 0.02658 -0.0638 0.0216 1.0000
11.250 1.3842 0.03645 0.02855 -0.0621 0.0206 1.0000
11.500 1.3846 0.03875 0.03093 -0.0603 0.0197 1.0000
11.750 1.3888 0.04080 0.03312 -0.0589 0.0190 1.0000
12.000 1.3934 0.04284 0.03530 -0.0576 0.0181 1.0000
12.250 1.3973 0.04499 0.03759 -0.0564 0.0173 1.0000
12.500 1.4006 0.04725 0.03997 -0.0553 0.0166 1.0000
12.750 1.4027 0.04968 0.04253 -0.0544 0.0160 1.0000
13.000 1.4031 0.05234 0.04530 -0.0536 0.0155 1.0000
13.250 1.4018 0.05527 0.04832 -0.0527 0.0151 1.0000
13.500 1.3991 0.05841 0.05156 -0.0519 0.0148 1.0000
13.750 1.3993 0.06133 0.05467 -0.0512 0.0145 1.0000
14.000 1.3983 0.06445 0.05797 -0.0507 0.0142 1.0000
14.250 1.3964 0.06778 0.06150 -0.0504 0.0139 1.0000
14.500 1.3935 0.07134 0.06525 -0.0504 0.0135 1.0000
14.750 1.3897 0.07514 0.06923 -0.0507 0.0132 1.0000
15.000 1.3850 0.07916 0.07343 -0.0512 0.0129 1.0000
15.250 1.3794 0.08345 0.07789 -0.0520 0.0126 1.0000
15.500 1.3732 0.08796 0.08256 -0.0532 0.0123 1.0000
15.750 1.3662 0.09272 0.08747 -0.0547 0.0121 1.0000
16.000 1.3585 0.09771 0.09262 -0.0564 0.0119 1.0000
16.250 1.3504 0.10291 0.09798 -0.0585 0.0117 1.0000
16.500 1.3414 0.10844 0.10367 -0.0608 0.0116 1.0000
16.750 1.3316 0.11426 0.10964 -0.0634 0.0115 1.0000
17.000 1.3209 0.12045 0.11598 -0.0664 0.0114 1.0000
17.250 1.3092 0.12705 0.12275 -0.0698 0.0113 1.0000
17.500 1.2965 0.13415 0.13002 -0.0737 0.0113 1.0000
17.750 1.2829 0.14180 0.13785 -0.0783 0.0112 1.0000
18.000 1.2680 0.15021 0.14643 -0.0836 0.0112 1.0000
18.250 1.2504 0.15989 0.15632 -0.0899 0.0112 1.0000
18.500 1.2124 0.17724 0.17397 -0.1016 0.0115 1.0000
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