AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.75 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5046-il-1000000.txt Download as CSV file: xf-as5046-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AS5046 (16%)
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.3715 0.13399 0.13156 -0.0306 0.7594 0.0118
-14.750 -0.5599 0.13751 0.13531 -0.0186 0.8289 0.0114
-14.500 -0.5603 0.13331 0.13096 -0.0202 0.7976 0.0115
-14.250 -0.5618 0.12824 0.12584 -0.0225 0.7862 0.0116
-14.000 -0.5667 0.12199 0.11956 -0.0253 0.7791 0.0116
-12.500 -0.8570 0.04555 0.04143 -0.0588 0.7619 0.0091
-12.250 -0.8570 0.04328 0.03905 -0.0586 0.7577 0.0092
-12.000 -0.8592 0.03998 0.03547 -0.0575 0.7541 0.0085
-11.750 -0.8633 0.03693 0.03219 -0.0566 0.7505 0.0085
-11.500 -0.7903 0.02182 0.01707 -0.0587 0.7439 0.0086
-11.250 -0.7887 0.01964 0.01471 -0.0576 0.7413 0.0086
-11.000 -0.7830 0.01727 0.01217 -0.0564 0.7388 0.0085
-10.750 -0.7742 0.01551 0.01023 -0.0554 0.7364 0.0086
-10.500 -0.7626 0.01409 0.00865 -0.0544 0.7341 0.0086
-10.250 -0.7481 0.01261 0.00704 -0.0535 0.7318 0.0086
-10.000 -0.7324 0.01142 0.00574 -0.0527 0.7303 0.0086
-9.750 -0.7702 0.02301 0.01695 -0.0492 0.7307 0.0086
-9.500 -0.7498 0.02202 0.01587 -0.0487 0.7291 0.0086
-9.250 -0.7291 0.02111 0.01488 -0.0481 0.7273 0.0086
-9.000 -0.7078 0.02031 0.01401 -0.0476 0.7255 0.0087
-8.750 -0.6897 0.01897 0.01261 -0.0466 0.7236 0.0088
-8.500 -0.6718 0.01788 0.01148 -0.0458 0.7217 0.0091
-8.250 -0.6510 0.01716 0.01073 -0.0453 0.7199 0.0093
-8.000 -0.6290 0.01654 0.01007 -0.0450 0.7181 0.0095
-7.750 -0.6066 0.01595 0.00942 -0.0447 0.7161 0.0097
-7.500 -0.5834 0.01536 0.00881 -0.0444 0.7148 0.0099
-7.250 -0.5596 0.01481 0.00823 -0.0443 0.7136 0.0102
-7.000 -0.5351 0.01430 0.00769 -0.0442 0.7122 0.0106
-6.750 -0.5098 0.01385 0.00720 -0.0441 0.7106 0.0110
-6.500 -0.4842 0.01342 0.00674 -0.0441 0.7089 0.0113
-6.250 -0.4597 0.01279 0.00607 -0.0441 0.7074 0.0119
-6.000 -0.4330 0.01243 0.00570 -0.0442 0.7059 0.0125
-5.750 -0.4059 0.01211 0.00536 -0.0444 0.7045 0.0133
-5.500 -0.3783 0.01186 0.00506 -0.0446 0.7030 0.0140
-5.250 -0.3513 0.01147 0.00465 -0.0448 0.7014 0.0156
-5.000 -0.3234 0.01122 0.00439 -0.0451 0.6994 0.0181
-4.750 -0.2955 0.01091 0.00410 -0.0454 0.6980 0.0232
-4.500 -0.2683 0.01036 0.00373 -0.0458 0.6969 0.0580
-4.250 -0.2437 0.00892 0.00305 -0.0467 0.6955 0.2366
-4.000 -0.2162 0.00775 0.00252 -0.0479 0.6938 0.3979
-3.750 -0.1868 0.00691 0.00224 -0.0491 0.6920 0.5423
-3.500 -0.1568 0.00686 0.00228 -0.0496 0.6901 0.5817
-3.250 -0.1266 0.00692 0.00233 -0.0500 0.6883 0.6002
-3.000 -0.0966 0.00703 0.00243 -0.0504 0.6864 0.6140
-2.750 -0.0664 0.00714 0.00247 -0.0509 0.6843 0.6210
-2.500 -0.0366 0.00723 0.00256 -0.0512 0.6818 0.6260
-2.250 -0.0066 0.00726 0.00259 -0.0516 0.6800 0.6305
-2.000 0.0235 0.00729 0.00259 -0.0521 0.6775 0.6341
-1.750 0.0536 0.00730 0.00256 -0.0525 0.6745 0.6368
-1.500 0.0832 0.00726 0.00251 -0.0529 0.6715 0.6398
-1.250 0.1130 0.00728 0.00252 -0.0532 0.6688 0.6422
-1.000 0.1428 0.00735 0.00256 -0.0537 0.6658 0.6445
-0.750 0.1728 0.00735 0.00256 -0.0541 0.6636 0.6468
-0.500 0.2027 0.00734 0.00255 -0.0545 0.6610 0.6488
-0.250 0.2327 0.00735 0.00254 -0.0550 0.6580 0.6508
0.000 0.2628 0.00737 0.00253 -0.0554 0.6548 0.6525
0.250 0.2922 0.00730 0.00244 -0.0558 0.6505 0.6549
0.500 0.3218 0.00725 0.00241 -0.0562 0.6456 0.6566
0.750 0.3515 0.00720 0.00238 -0.0565 0.6406 0.6580
1.000 0.3811 0.00718 0.00235 -0.0569 0.6360 0.6594
1.250 0.4107 0.00718 0.00235 -0.0573 0.6314 0.6607
1.500 0.4406 0.00715 0.00235 -0.0577 0.6265 0.6622
1.750 0.4703 0.00715 0.00234 -0.0581 0.6210 0.6637
2.000 0.4998 0.00715 0.00234 -0.0585 0.6149 0.6651
2.250 0.5294 0.00714 0.00233 -0.0589 0.6064 0.6663
2.500 0.5588 0.00716 0.00234 -0.0593 0.5981 0.6675
2.750 0.5880 0.00720 0.00235 -0.0596 0.5866 0.6686
3.000 0.6169 0.00725 0.00236 -0.0598 0.5708 0.6697
3.250 0.6451 0.00729 0.00236 -0.0600 0.5505 0.6714
3.500 0.6724 0.00744 0.00242 -0.0600 0.5221 0.6727
3.750 0.6988 0.00770 0.00255 -0.0599 0.4855 0.6740
4.000 0.7244 0.00804 0.00273 -0.0596 0.4455 0.6753
4.250 0.7499 0.00839 0.00294 -0.0594 0.4093 0.6767
4.500 0.7762 0.00868 0.00313 -0.0592 0.3801 0.6781
4.750 0.8021 0.00899 0.00332 -0.0591 0.3514 0.6795
5.000 0.8278 0.00931 0.00354 -0.0589 0.3242 0.6808
5.250 0.8537 0.00962 0.00375 -0.0588 0.2996 0.6820
5.500 0.8790 0.00997 0.00398 -0.0585 0.2724 0.6833
5.750 0.9038 0.01035 0.00424 -0.0582 0.2466 0.6846
6.000 0.9294 0.01067 0.00447 -0.0580 0.2271 0.6857
6.250 0.9547 0.01097 0.00470 -0.0578 0.2094 0.6871
6.500 0.9800 0.01124 0.00493 -0.0576 0.1950 0.6887
6.750 1.0051 0.01153 0.00519 -0.0573 0.1822 0.6902
7.250 1.0555 0.01210 0.00571 -0.0568 0.1611 0.6929
7.500 1.0804 0.01240 0.00600 -0.0565 0.1516 0.6945
7.750 1.1047 0.01273 0.00629 -0.0561 0.1418 0.6961
8.000 1.1294 0.01302 0.00658 -0.0558 0.1334 0.6977
8.250 1.1532 0.01338 0.00691 -0.0553 0.1243 0.6992
8.500 1.1765 0.01375 0.00724 -0.0548 0.1147 0.7006
8.750 1.1998 0.01411 0.00758 -0.0543 0.1060 0.7018
9.000 1.2220 0.01452 0.00796 -0.0536 0.0970 0.7031
9.500 1.2646 0.01537 0.00878 -0.0521 0.0807 0.7069
9.750 1.2850 0.01584 0.00925 -0.0511 0.0740 0.7086
10.000 1.3042 0.01635 0.00975 -0.0500 0.0677 0.7103
10.250 1.3237 0.01682 0.01023 -0.0490 0.0626 0.7122
10.500 1.3405 0.01741 0.01080 -0.0475 0.0574 0.7142
10.750 1.3549 0.01788 0.01131 -0.0455 0.0540 0.7161
11.000 1.3690 0.01849 0.01192 -0.0437 0.0504 0.7178
11.250 1.3833 0.01918 0.01262 -0.0420 0.0470 0.7195
11.500 1.3991 0.01978 0.01328 -0.0407 0.0448 0.7219
11.750 1.4122 0.02058 0.01411 -0.0391 0.0423 0.7242
12.000 1.4241 0.02151 0.01509 -0.0376 0.0399 0.7264
12.250 1.4390 0.02231 0.01595 -0.0366 0.0383 0.7288
12.500 1.4515 0.02334 0.01702 -0.0356 0.0365 0.7311
12.750 1.4614 0.02467 0.01838 -0.0346 0.0346 0.7334
13.000 1.4736 0.02588 0.01965 -0.0339 0.0332 0.7355
13.250 1.4872 0.02699 0.02085 -0.0335 0.0320 0.7387
13.500 1.4986 0.02833 0.02225 -0.0329 0.0306 0.7417
13.750 1.5068 0.02993 0.02390 -0.0322 0.0292 0.7449
14.000 1.5143 0.03161 0.02565 -0.0314 0.0281 0.7483
14.250 1.5257 0.03294 0.02706 -0.0309 0.0272 0.7517
14.500 1.5350 0.03446 0.02866 -0.0304 0.0263 0.7563
14.750 1.5420 0.03618 0.03045 -0.0298 0.0254 0.7611
15.000 1.5457 0.03822 0.03254 -0.0291 0.0244 0.7662
15.250 1.5465 0.04054 0.03497 -0.0283 0.0235 0.7722
15.500 1.5536 0.04230 0.03684 -0.0279 0.0231 0.7804
15.750 1.5593 0.04422 0.03888 -0.0275 0.0224 0.7911
16.000 1.5639 0.04628 0.04107 -0.0272 0.0218 0.8085
16.250 1.5660 0.04861 0.04362 -0.0269 0.0212 0.8545
16.500 1.5567 0.05065 0.04592 -0.0243 0.0207 1.0000
16.750 1.5530 0.05388 0.04922 -0.0243 0.0200 1.0000
17.000 1.5480 0.05735 0.05278 -0.0245 0.0195 1.0000
17.250 1.5500 0.06011 0.05563 -0.0247 0.0192 1.0000
17.500 1.5498 0.06321 0.05882 -0.0251 0.0188 1.0000
17.750 1.5481 0.06659 0.06229 -0.0257 0.0184 1.0000
18.000 1.5444 0.07028 0.06608 -0.0265 0.0180 1.0000
18.250 1.5383 0.07437 0.07025 -0.0274 0.0176 1.0000
18.500 1.5305 0.07880 0.07478 -0.0286 0.0173 1.0000
18.750 1.5195 0.08380 0.07987 -0.0301 0.0169 1.0000
19.000 1.5044 0.08950 0.08567 -0.0320 0.0166 1.0000
19.250 1.4855 0.09588 0.09218 -0.0342 0.0163 1.0000
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Polar data table (+)
Polar graphs
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