AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AS5048 (18%) (as5048-il) Reynolds number: 200,000 Max Cl/Cd: 56.31 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-as5048-il-200000-n5.txt Download as CSV file: xf-as5048-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AS5048 (18%)
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6483 0.11030 0.10602 -0.0454 1.0000 0.0131
-15.250 -0.6704 0.10145 0.09704 -0.0505 1.0000 0.0131
-15.000 -0.6929 0.09339 0.08883 -0.0548 1.0000 0.0130
-14.750 -0.7143 0.08633 0.08161 -0.0583 1.0000 0.0129
-14.500 -0.7340 0.08023 0.07534 -0.0608 1.0000 0.0129
-14.250 -0.7537 0.07470 0.06962 -0.0625 1.0000 0.0129
-14.000 -0.7715 0.06983 0.06456 -0.0634 1.0000 0.0129
-13.750 -0.7883 0.06534 0.05987 -0.0638 1.0000 0.0129
-13.500 -0.8026 0.06133 0.05565 -0.0637 1.0000 0.0129
-13.250 -0.8154 0.05762 0.05171 -0.0631 1.0000 0.0129
-13.000 -0.8250 0.05433 0.04819 -0.0621 1.0000 0.0130
-12.750 -0.8326 0.05130 0.04493 -0.0609 1.0000 0.0130
-12.500 -0.8376 0.04854 0.04193 -0.0595 1.0000 0.0131
-12.250 -0.8393 0.04611 0.03928 -0.0580 1.0000 0.0132
-12.000 -0.8288 0.04389 0.03695 -0.0578 0.9981 0.0134
-11.750 -0.8141 0.04173 0.03469 -0.0579 0.9337 0.0136
-11.500 -0.7668 0.03901 0.03171 -0.0652 0.8992 0.0139
-11.250 -0.7159 0.03658 0.02893 -0.0725 0.8663 0.0144
-10.750 -0.6622 0.03373 0.02549 -0.0754 0.8241 0.0157
-10.500 -0.6405 0.03258 0.02410 -0.0754 0.8135 0.0163
-10.250 -0.6187 0.03154 0.02302 -0.0755 0.8054 0.0169
-10.000 -0.5985 0.03058 0.02199 -0.0753 0.7990 0.0174
-9.750 -0.5787 0.02965 0.02097 -0.0748 0.7935 0.0179
-9.500 -0.5600 0.02873 0.01997 -0.0742 0.7890 0.0185
-9.250 -0.5425 0.02783 0.01897 -0.0734 0.7851 0.0190
-9.000 -0.5258 0.02693 0.01799 -0.0726 0.7813 0.0196
-8.750 -0.5117 0.02590 0.01695 -0.0717 0.7777 0.0202
-8.500 -0.4967 0.02497 0.01599 -0.0710 0.7743 0.0210
-8.250 -0.4807 0.02414 0.01510 -0.0703 0.7711 0.0222
-8.000 -0.4644 0.02334 0.01419 -0.0696 0.7682 0.0235
-7.750 -0.4512 0.02235 0.01320 -0.0686 0.7650 0.0245
-7.500 -0.4365 0.02153 0.01232 -0.0676 0.7621 0.0257
-7.250 -0.4218 0.02082 0.01155 -0.0664 0.7595 0.0270
-7.000 -0.4082 0.02023 0.01089 -0.0648 0.7570 0.0287
-6.750 -0.3937 0.01969 0.01030 -0.0632 0.7548 0.0312
-6.500 -0.3763 0.01917 0.00971 -0.0621 0.7527 0.0344
-6.250 -0.3587 0.01865 0.00915 -0.0609 0.7504 0.0392
-6.000 -0.3428 0.01800 0.00858 -0.0595 0.7478 0.0512
-5.750 -0.3377 0.01667 0.00776 -0.0568 0.7453 0.1377
-5.500 -0.3350 0.01512 0.00692 -0.0539 0.7430 0.2764
-5.250 -0.3302 0.01371 0.00629 -0.0509 0.7409 0.4272
-5.000 -0.3114 0.01357 0.00675 -0.0490 0.7390 0.5423
-4.750 -0.2845 0.01387 0.00705 -0.0486 0.7370 0.5840
-4.500 -0.2565 0.01433 0.00745 -0.0483 0.7352 0.6091
-4.250 -0.2287 0.01479 0.00787 -0.0479 0.7332 0.6254
-4.000 -0.2018 0.01502 0.00801 -0.0478 0.7313 0.6371
-3.750 -0.1732 0.01526 0.00822 -0.0477 0.7292 0.6417
-3.500 -0.1454 0.01534 0.00824 -0.0477 0.7269 0.6467
-3.250 -0.1182 0.01529 0.00804 -0.0480 0.7247 0.6528
-3.000 -0.0896 0.01537 0.00808 -0.0481 0.7227 0.6555
-2.750 -0.0610 0.01544 0.00811 -0.0483 0.7208 0.6583
-2.500 -0.0324 0.01549 0.00808 -0.0485 0.7189 0.6615
-2.250 -0.0041 0.01550 0.00801 -0.0488 0.7170 0.6651
-2.000 0.0228 0.01544 0.00789 -0.0490 0.7145 0.6694
-1.750 0.0502 0.01545 0.00788 -0.0491 0.7119 0.6717
-1.500 0.0779 0.01548 0.00791 -0.0492 0.7093 0.6738
-1.250 0.1060 0.01549 0.00790 -0.0493 0.7067 0.6761
-1.000 0.1344 0.01549 0.00786 -0.0496 0.7043 0.6784
-0.750 0.1632 0.01549 0.00780 -0.0500 0.7021 0.6809
-0.500 0.1919 0.01549 0.00774 -0.0505 0.6997 0.6835
-0.250 0.2185 0.01545 0.00770 -0.0506 0.6962 0.6860
0.000 0.2457 0.01542 0.00767 -0.0507 0.6924 0.6880
0.250 0.2735 0.01540 0.00765 -0.0508 0.6887 0.6895
0.500 0.3024 0.01536 0.00758 -0.0511 0.6852 0.6910
0.750 0.3302 0.01535 0.00757 -0.0512 0.6814 0.6926
1.000 0.3562 0.01534 0.00761 -0.0510 0.6765 0.6946
1.250 0.3838 0.01531 0.00759 -0.0511 0.6722 0.6967
1.500 0.4126 0.01526 0.00752 -0.0514 0.6685 0.6986
1.750 0.4412 0.01522 0.00747 -0.0518 0.6648 0.7005
2.000 0.4670 0.01520 0.00750 -0.0516 0.6590 0.7027
2.250 0.4947 0.01514 0.00745 -0.0518 0.6539 0.7046
2.500 0.5236 0.01503 0.00733 -0.0519 0.6492 0.7060
2.750 0.5476 0.01495 0.00735 -0.0513 0.6403 0.7074
3.000 0.5753 0.01478 0.00717 -0.0512 0.6328 0.7089
3.250 0.6000 0.01472 0.00721 -0.0507 0.6230 0.7105
3.500 0.6272 0.01461 0.00710 -0.0506 0.6156 0.7124
3.750 0.6526 0.01458 0.00716 -0.0503 0.6052 0.7145
4.000 0.6789 0.01453 0.00715 -0.0501 0.5954 0.7166
4.250 0.7052 0.01446 0.00708 -0.0499 0.5843 0.7185
4.500 0.7308 0.01442 0.00706 -0.0495 0.5695 0.7203
4.750 0.7556 0.01438 0.00701 -0.0490 0.5524 0.7218
5.000 0.7795 0.01438 0.00701 -0.0482 0.5323 0.7232
5.250 0.8017 0.01446 0.00702 -0.0472 0.5077 0.7250
5.500 0.8222 0.01465 0.00711 -0.0458 0.4801 0.7270
5.750 0.8412 0.01494 0.00728 -0.0443 0.4524 0.7290
6.000 0.8593 0.01530 0.00754 -0.0427 0.4244 0.7311
6.250 0.8765 0.01572 0.00784 -0.0410 0.3971 0.7331
6.500 0.8920 0.01620 0.00820 -0.0390 0.3709 0.7351
6.750 0.9077 0.01669 0.00860 -0.0372 0.3454 0.7371
7.000 0.9215 0.01720 0.00903 -0.0350 0.3226 0.7388
7.250 0.9346 0.01767 0.00947 -0.0327 0.3026 0.7407
7.500 0.9465 0.01816 0.00994 -0.0302 0.2841 0.7429
7.750 0.9588 0.01871 0.01046 -0.0279 0.2669 0.7453
8.000 0.9722 0.01932 0.01105 -0.0259 0.2507 0.7479
8.250 0.9857 0.01999 0.01169 -0.0241 0.2359 0.7504
8.500 0.9986 0.02071 0.01239 -0.0224 0.2222 0.7529
8.750 1.0116 0.02145 0.01312 -0.0207 0.2095 0.7552
9.000 1.0247 0.02217 0.01387 -0.0191 0.1983 0.7574
9.250 1.0368 0.02299 0.01471 -0.0175 0.1888 0.7599
9.500 1.0493 0.02384 0.01560 -0.0162 0.1793 0.7626
9.750 1.0626 0.02471 0.01652 -0.0150 0.1712 0.7655
10.000 1.0745 0.02573 0.01755 -0.0139 0.1630 0.7687
10.250 1.0881 0.02667 0.01855 -0.0130 0.1552 0.7720
10.500 1.0991 0.02776 0.01969 -0.0119 0.1478 0.7753
10.750 1.1122 0.02876 0.02079 -0.0111 0.1407 0.7792
11.000 1.1229 0.02996 0.02202 -0.0102 0.1334 0.7833
11.250 1.1356 0.03106 0.02319 -0.0094 0.1266 0.7876
11.500 1.1456 0.03231 0.02450 -0.0085 0.1197 0.7919
11.750 1.1565 0.03350 0.02579 -0.0076 0.1133 0.7971
12.000 1.1657 0.03484 0.02719 -0.0067 0.1070 0.8031
12.250 1.1748 0.03617 0.02860 -0.0058 0.1013 0.8100
12.500 1.1827 0.03756 0.03008 -0.0048 0.0955 0.8190
12.750 1.1884 0.03906 0.03167 -0.0036 0.0907 0.8310
13.000 1.1933 0.04036 0.03314 -0.0019 0.0861 0.8525
13.250 1.1819 0.04124 0.03422 0.0030 0.0833 1.0000
13.500 1.1883 0.04307 0.03608 0.0034 0.0793 1.0000
13.750 1.1961 0.04479 0.03788 0.0038 0.0753 1.0000
14.000 1.2007 0.04683 0.03995 0.0042 0.0718 1.0000
14.250 1.2051 0.04893 0.04209 0.0046 0.0688 1.0000
14.500 1.2115 0.05091 0.04417 0.0048 0.0657 1.0000
14.750 1.2152 0.05316 0.04648 0.0050 0.0628 1.0000
15.000 1.2162 0.05577 0.04913 0.0051 0.0605 1.0000
15.250 1.2206 0.05809 0.05155 0.0051 0.0582 1.0000
15.500 1.2243 0.06054 0.05411 0.0050 0.0559 1.0000
15.750 1.2256 0.06331 0.05695 0.0048 0.0539 1.0000
16.000 1.2244 0.06644 0.06012 0.0044 0.0522 1.0000
16.250 1.2245 0.06947 0.06324 0.0040 0.0505 1.0000
16.500 1.2259 0.07240 0.06631 0.0035 0.0489 1.0000
16.750 1.2257 0.07563 0.06964 0.0028 0.0473 1.0000
17.000 1.2237 0.07914 0.07324 0.0020 0.0459 1.0000
17.250 1.2195 0.08298 0.07716 0.0009 0.0447 1.0000
17.500 1.2152 0.08687 0.08111 -0.0002 0.0436 1.0000
17.750 1.2136 0.09051 0.08490 -0.0013 0.0424 1.0000
18.000 1.2105 0.09440 0.08892 -0.0026 0.0412 1.0000
18.250 1.2064 0.09848 0.09312 -0.0040 0.0402 1.0000
18.500 1.2013 0.10277 0.09751 -0.0057 0.0392 1.0000
18.750 1.1956 0.10720 0.10203 -0.0076 0.0383 1.0000
19.000 1.1897 0.11167 0.10655 -0.0095 0.0375 1.0000
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