USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 32 AIRFOIL (usa32-il) Reynolds number: 100,000 Max Cl/Cd: 41.03 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa32-il-100000-n5.txt Download as CSV file: xf-usa32-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 32 AIRFOIL
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 0.0890 0.10765 0.10244 -0.1083 0.8876 0.0673
-9.000 0.0850 0.10577 0.10057 -0.1140 0.8841 0.0699
-8.750 0.0656 0.10533 0.10021 -0.1106 0.8723 0.0701
-8.500 0.0884 0.10069 0.09556 -0.1114 0.8700 0.0709
-8.250 0.1159 0.09700 0.09184 -0.1124 0.8681 0.0732
-8.000 0.1124 0.09563 0.09051 -0.1100 0.8590 0.0754
-7.500 0.0694 0.09424 0.08922 -0.1086 0.8376 0.0805
-7.000 0.1059 0.08648 0.08144 -0.1101 0.8316 0.0828
-6.750 0.0934 0.08543 0.08045 -0.1054 0.8185 0.0834
-6.500 0.1081 0.08231 0.07730 -0.1068 0.8145 0.0850
-6.000 0.0643 0.07415 0.06903 -0.1055 0.7851 0.0612
-5.750 0.0784 0.07094 0.06577 -0.1060 0.7807 0.0615
-5.000 0.0820 0.06061 0.05519 -0.1033 0.7519 0.0528
-4.750 0.0993 0.05744 0.05191 -0.1038 0.7476 0.0522
-4.500 0.1028 0.05502 0.04940 -0.1021 0.7379 0.0517
-4.250 0.1179 0.05031 0.04446 -0.1031 0.7325 0.0518
-4.000 0.1351 0.04242 0.03602 -0.1055 0.7295 0.0516
-3.750 0.1354 0.03855 0.03162 -0.1029 0.7191 0.0510
-3.500 0.1572 0.03501 0.02742 -0.1025 0.7153 0.0509
-3.250 0.1763 0.03306 0.02500 -0.1011 0.7097 0.0510
-3.000 0.1947 0.03174 0.02329 -0.0994 0.7030 0.0513
-2.750 0.2247 0.03020 0.02128 -0.0993 0.6994 0.0525
-2.500 0.2582 0.02877 0.01951 -0.0999 0.6964 0.0536
-2.250 0.2739 0.02836 0.01899 -0.0977 0.6884 0.0542
-2.000 0.3061 0.02735 0.01779 -0.0980 0.6842 0.0547
-1.750 0.3442 0.02624 0.01652 -0.0993 0.6811 0.0556
-1.500 0.3652 0.02595 0.01613 -0.0979 0.6744 0.0563
-1.250 0.3954 0.02536 0.01543 -0.0980 0.6691 0.0573
-1.000 0.4342 0.02460 0.01452 -0.0995 0.6652 0.0589
-0.750 0.4637 0.02427 0.01406 -0.0995 0.6598 0.0613
-0.500 0.4890 0.02402 0.01378 -0.0990 0.6533 0.0637
-0.250 0.5283 0.02350 0.01314 -0.1008 0.6487 0.0663
0.000 0.5667 0.02313 0.01261 -0.1025 0.6437 0.0694
0.250 0.5891 0.02312 0.01259 -0.1015 0.6368 0.0733
0.500 0.6355 0.02263 0.01209 -0.1050 0.6313 0.0890
0.750 0.6870 0.02241 0.01220 -0.1097 0.6264 0.2088
1.000 0.6947 0.02290 0.01269 -0.1058 0.6189 0.2298
1.250 0.7203 0.02308 0.01277 -0.1052 0.6130 0.2483
1.500 0.7547 0.02316 0.01271 -0.1062 0.6082 0.2641
1.750 0.7582 0.02372 0.01326 -0.1018 0.6005 0.2746
2.000 0.7805 0.02395 0.01346 -0.1006 0.5942 0.2858
2.250 0.8108 0.02408 0.01348 -0.1010 0.5889 0.3004
2.500 0.8132 0.02464 0.01410 -0.0965 0.5810 0.3070
2.750 0.8452 0.02475 0.01406 -0.0974 0.5747 0.3144
3.000 0.8772 0.02489 0.01416 -0.0985 0.5688 0.3192
3.250 0.8892 0.02536 0.01466 -0.0961 0.5609 0.3230
3.500 0.9236 0.02541 0.01460 -0.0975 0.5549 0.3289
3.750 0.9369 0.02584 0.01503 -0.0953 0.5475 0.3331
4.000 0.9538 0.02616 0.01536 -0.0936 0.5401 0.3375
4.250 0.9845 0.02616 0.01527 -0.0943 0.5347 0.3454
4.500 0.9843 0.02689 0.01607 -0.0898 0.5260 0.3499
4.750 1.0067 0.02703 0.01620 -0.0891 0.5201 0.3562
5.000 1.0196 0.02748 0.01663 -0.0869 0.5135 0.3630
5.250 1.0311 0.02793 0.01713 -0.0845 0.5064 0.3684
5.500 1.0557 0.02797 0.01708 -0.0841 0.5013 0.3765
5.750 1.0598 0.02871 0.01789 -0.0807 0.4936 0.3826
6.000 1.0764 0.02901 0.01816 -0.0791 0.4876 0.3913
6.250 1.0972 0.02916 0.01829 -0.0781 0.4825 0.4010
6.500 1.1039 0.02994 0.01912 -0.0753 0.4757 0.4093
6.750 1.1233 0.03019 0.01937 -0.0743 0.4707 0.4211
7.000 1.1489 0.03024 0.01940 -0.0742 0.4666 0.4352
7.250 1.1537 0.03120 0.02048 -0.0714 0.4602 0.4478
7.750 1.3027 0.03175 0.02189 -0.0921 0.4489 1.0000
8.000 1.3067 0.03280 0.02300 -0.0891 0.4432 1.0000
8.250 1.3212 0.03341 0.02361 -0.0874 0.4384 1.0000
8.500 1.3450 0.03362 0.02374 -0.0870 0.4346 1.0000
8.750 1.3524 0.03458 0.02474 -0.0846 0.4295 1.0000
9.000 1.3578 0.03565 0.02586 -0.0819 0.4241 1.0000
9.250 1.3752 0.03609 0.02628 -0.0807 0.4191 1.0000
9.500 1.3941 0.03651 0.02665 -0.0798 0.4144 1.0000
9.750 1.3908 0.03810 0.02836 -0.0763 0.4091 1.0000
10.000 1.4008 0.03901 0.02930 -0.0744 0.4042 1.0000
10.250 1.4232 0.03924 0.02950 -0.0739 0.4001 1.0000
10.500 1.4277 0.04049 0.03082 -0.0715 0.3953 1.0000
10.750 1.4219 0.04236 0.03281 -0.0682 0.3896 1.0000
11.000 1.4341 0.04315 0.03361 -0.0668 0.3847 1.0000
11.250 1.4608 0.04313 0.03355 -0.0667 0.3812 1.0000
11.500 1.4468 0.04571 0.03632 -0.0630 0.3762 1.0000
11.750 1.4399 0.04799 0.03874 -0.0602 0.3714 1.0000
12.000 1.4507 0.04901 0.03980 -0.0589 0.3672 1.0000
12.250 1.4763 0.04893 0.03969 -0.0587 0.3638 1.0000
12.500 1.4545 0.05251 0.04347 -0.0552 0.3585 1.0000
12.750 1.4371 0.05599 0.04710 -0.0523 0.3525 1.0000
13.000 1.4524 0.05664 0.04779 -0.0515 0.3484 1.0000
13.250 1.4853 0.05575 0.04687 -0.0516 0.3452 1.0000
13.500 1.4097 0.06524 0.05670 -0.0469 0.3363 1.0000
13.750 1.4190 0.06652 0.05804 -0.0460 0.3316 1.0000
14.000 1.4559 0.06480 0.05628 -0.0459 0.3283 1.0000
14.250 1.3567 0.07863 0.07045 -0.0430 0.3161 1.0000
14.500 1.3967 0.07608 0.06786 -0.0426 0.3127 1.0000
14.750 1.3118 0.08958 0.08159 -0.0417 0.2989 1.0000
15.000 1.3528 0.08656 0.07858 -0.0410 0.2960 1.0000
15.500 1.3270 0.09518 0.08736 -0.0403 0.2792 1.0000
16.000 1.3115 0.10278 0.09510 -0.0402 0.2628 1.0000
16.500 1.3017 0.10979 0.10223 -0.0404 0.2472 1.0000
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Polar data table (+)
Polar graphs
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