USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 200,000 Max Cl/Cd: 69 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27-il-200000-n5.txt Download as CSV file: xf-usa27-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2641 0.09195 0.08855 -0.0532 0.9850 0.0346
-8.250 -0.2606 0.08673 0.08334 -0.0618 0.9761 0.0350
-8.000 -0.2520 0.08118 0.07778 -0.0679 0.9682 0.0353
-7.750 -0.2362 0.07906 0.07567 -0.0659 0.9660 0.0362
-7.250 -0.2055 0.07255 0.06912 -0.0719 0.9550 0.0387
-7.000 -0.1860 0.06791 0.06443 -0.0782 0.9501 0.0405
-6.750 -0.1715 0.05888 0.05510 -0.0898 0.9383 0.0433
-6.500 -0.1533 0.05667 0.05292 -0.0898 0.9358 0.0441
-6.250 -0.1358 0.05506 0.05131 -0.0898 0.9308 0.0455
-6.000 -0.1169 0.05244 0.04861 -0.0911 0.9238 0.0481
-5.500 -0.0855 0.03509 0.02999 -0.0961 0.9072 0.0348
-5.250 -0.0671 0.03155 0.02604 -0.0959 0.8991 0.0358
-5.000 -0.0419 0.02897 0.02305 -0.0960 0.8904 0.0356
-4.500 0.0107 0.02534 0.01878 -0.0957 0.8716 0.0349
-4.250 0.0344 0.02372 0.01687 -0.0950 0.8615 0.0349
-4.000 0.0606 0.02232 0.01519 -0.0947 0.8521 0.0349
-3.750 0.0895 0.02086 0.01341 -0.0949 0.8432 0.0355
-3.500 0.1145 0.01956 0.01195 -0.0945 0.8319 0.0362
-3.250 0.1424 0.01860 0.01079 -0.0943 0.8206 0.0364
-3.000 0.1713 0.01774 0.00973 -0.0943 0.8086 0.0364
-2.750 0.1999 0.01697 0.00879 -0.0942 0.7952 0.0364
-2.500 0.2273 0.01631 0.00799 -0.0939 0.7795 0.0366
-2.250 0.2540 0.01572 0.00729 -0.0935 0.7617 0.0368
-2.000 0.2806 0.01520 0.00667 -0.0931 0.7421 0.0371
-1.750 0.3071 0.01476 0.00612 -0.0926 0.7216 0.0375
-1.500 0.3329 0.01440 0.00565 -0.0920 0.7003 0.0379
-1.250 0.3579 0.01414 0.00526 -0.0913 0.6797 0.0388
-1.000 0.3824 0.01395 0.00496 -0.0905 0.6614 0.0402
-0.750 0.4067 0.01380 0.00470 -0.0896 0.6453 0.0411
-0.500 0.4309 0.01368 0.00448 -0.0888 0.6311 0.0415
-0.250 0.4553 0.01360 0.00430 -0.0880 0.6182 0.0419
0.000 0.4798 0.01356 0.00415 -0.0872 0.6058 0.0425
0.500 0.5285 0.01349 0.00390 -0.0857 0.5799 0.0444
0.750 0.5526 0.01348 0.00382 -0.0849 0.5665 0.0462
1.000 0.5767 0.01348 0.00378 -0.0840 0.5529 0.0487
1.250 0.6004 0.01348 0.00375 -0.0832 0.5392 0.0563
1.500 0.6206 0.01310 0.00384 -0.0818 0.5251 0.2215
1.750 0.6428 0.01308 0.00392 -0.0807 0.5094 0.2848
2.000 0.6651 0.01310 0.00399 -0.0797 0.4935 0.3387
2.250 0.6827 0.01257 0.00403 -0.0779 0.4790 0.5782
2.750 0.8129 0.01272 0.00466 -0.0939 0.4418 1.0000
3.000 0.8330 0.01295 0.00479 -0.0924 0.4316 1.0000
3.250 0.8532 0.01318 0.00493 -0.0909 0.4220 1.0000
3.500 0.8739 0.01339 0.00508 -0.0896 0.4142 1.0000
3.750 0.8946 0.01362 0.00525 -0.0882 0.4071 1.0000
4.000 0.9153 0.01385 0.00542 -0.0868 0.4007 1.0000
4.250 0.9362 0.01406 0.00561 -0.0855 0.3939 1.0000
4.750 0.9775 0.01453 0.00602 -0.0829 0.3810 1.0000
5.000 0.9978 0.01477 0.00623 -0.0815 0.3747 1.0000
5.250 1.0183 0.01502 0.00646 -0.0801 0.3688 1.0000
5.500 1.0387 0.01525 0.00670 -0.0788 0.3620 1.0000
5.750 1.0583 0.01553 0.00695 -0.0773 0.3562 1.0000
6.000 1.0795 0.01575 0.00721 -0.0761 0.3511 1.0000
6.250 1.1001 0.01600 0.00750 -0.0748 0.3458 1.0000
6.500 1.1200 0.01629 0.00779 -0.0735 0.3408 1.0000
6.750 1.1406 0.01653 0.00809 -0.0722 0.3350 1.0000
7.000 1.1582 0.01683 0.00837 -0.0704 0.3255 1.0000
7.250 1.1758 0.01709 0.00867 -0.0687 0.3139 1.0000
7.500 1.1927 0.01741 0.00899 -0.0668 0.3028 1.0000
7.750 1.2081 0.01775 0.00932 -0.0647 0.2927 1.0000
8.000 1.2241 0.01808 0.00967 -0.0627 0.2794 1.0000
8.250 1.2388 0.01847 0.01007 -0.0606 0.2641 1.0000
8.500 1.2516 0.01897 0.01051 -0.0582 0.2407 1.0000
8.750 1.2608 0.01969 0.01108 -0.0554 0.2113 1.0000
9.000 1.2676 0.02065 0.01185 -0.0524 0.1852 1.0000
9.250 1.2761 0.02159 0.01270 -0.0498 0.1684 1.0000
9.500 1.2860 0.02249 0.01358 -0.0475 0.1547 1.0000
9.750 1.2932 0.02358 0.01459 -0.0449 0.1351 1.0000
10.000 1.2932 0.02516 0.01591 -0.0417 0.0921 1.0000
10.250 1.2721 0.02825 0.01855 -0.0365 0.0297 1.0000
10.500 1.2736 0.02996 0.02028 -0.0340 0.0231 1.0000
10.750 1.2798 0.03138 0.02180 -0.0321 0.0212 1.0000
11.000 1.2850 0.03293 0.02347 -0.0302 0.0199 1.0000
11.250 1.2889 0.03466 0.02535 -0.0285 0.0188 1.0000
11.500 1.2938 0.03638 0.02720 -0.0270 0.0181 1.0000
11.750 1.2979 0.03823 0.02920 -0.0257 0.0174 1.0000
12.000 1.3004 0.04031 0.03143 -0.0244 0.0166 1.0000
12.250 1.3011 0.04266 0.03392 -0.0234 0.0160 1.0000
12.500 1.3000 0.04531 0.03672 -0.0226 0.0155 1.0000
12.750 1.2972 0.04829 0.03986 -0.0220 0.0151 1.0000
13.000 1.2924 0.05167 0.04342 -0.0217 0.0148 1.0000
13.250 1.2853 0.05549 0.04740 -0.0217 0.0146 1.0000
13.500 1.2761 0.05973 0.05180 -0.0220 0.0144 1.0000
13.750 1.2651 0.06435 0.05659 -0.0226 0.0142 1.0000
14.000 1.2528 0.06932 0.06171 -0.0234 0.0141 1.0000
14.250 1.2409 0.07436 0.06688 -0.0245 0.0139 1.0000
14.500 1.2324 0.07901 0.07167 -0.0255 0.0139 1.0000
14.750 1.2242 0.08372 0.07651 -0.0266 0.0137 1.0000
15.000 1.2162 0.08844 0.08135 -0.0278 0.0136 1.0000
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