USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 28 AIRFOIL (usa28-il) Reynolds number: 100,000 Max Cl/Cd: 54.42 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa28-il-100000-n5.txt Download as CSV file: xf-usa28-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 28 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4463 0.10469 0.09935 -0.0482 1.0000 0.0484
-11.250 -0.6110 0.06856 0.06323 -0.0702 1.0000 0.0456
-11.000 -0.6468 0.06131 0.05594 -0.0747 1.0000 0.0453
-10.750 -0.6799 0.05664 0.05120 -0.0758 1.0000 0.0450
-10.500 -0.7129 0.05375 0.04822 -0.0722 1.0000 0.0449
-10.250 -0.7377 0.05080 0.04510 -0.0688 1.0000 0.0450
-10.000 -0.7580 0.04816 0.04220 -0.0650 1.0000 0.0454
-9.750 -0.7713 0.04570 0.03950 -0.0613 1.0000 0.0458
-9.500 -0.7515 0.04298 0.03668 -0.0630 0.9953 0.0472
-9.250 -0.7299 0.04095 0.03449 -0.0644 0.9898 0.0489
-9.000 -0.7079 0.03884 0.03209 -0.0658 0.9843 0.0510
-8.750 -0.6881 0.03665 0.02953 -0.0664 0.9776 0.0527
-8.500 -0.6671 0.03463 0.02713 -0.0668 0.9714 0.0543
-8.250 -0.6431 0.03306 0.02510 -0.0673 0.9654 0.0562
-8.000 -0.6226 0.03126 0.02325 -0.0670 0.9590 0.0581
-7.750 -0.5970 0.02992 0.02181 -0.0675 0.9537 0.0599
-7.500 -0.5743 0.02873 0.02048 -0.0672 0.9472 0.0616
-7.250 -0.5479 0.02758 0.01916 -0.0674 0.9415 0.0636
-7.000 -0.5221 0.02659 0.01795 -0.0675 0.9357 0.0664
-6.750 -0.4962 0.02572 0.01688 -0.0674 0.9292 0.0689
-6.500 -0.4673 0.02453 0.01570 -0.0682 0.9251 0.0724
-6.250 -0.4461 0.02379 0.01487 -0.0672 0.9172 0.0751
-6.000 -0.4170 0.02298 0.01393 -0.0677 0.9125 0.0795
-5.750 -0.3891 0.02218 0.01305 -0.0679 0.9078 0.0846
-5.500 -0.3656 0.02151 0.01237 -0.0673 0.9008 0.0920
-5.250 -0.3348 0.02077 0.01176 -0.0682 0.8967 0.1096
-5.000 -0.3041 0.02026 0.01125 -0.0689 0.8922 0.1397
-4.750 -0.2780 0.01991 0.01078 -0.0686 0.8850 0.1634
-4.500 -0.2444 0.01946 0.01031 -0.0699 0.8809 0.1857
-4.250 -0.2128 0.01910 0.00993 -0.0707 0.8756 0.2048
-4.000 -0.1848 0.01885 0.00966 -0.0708 0.8684 0.2243
-3.750 -0.1474 0.01853 0.00936 -0.0727 0.8642 0.2457
-3.500 -0.1200 0.01841 0.00924 -0.0726 0.8562 0.2646
-3.250 -0.0846 0.01825 0.00905 -0.0739 0.8504 0.2856
-3.000 -0.0479 0.01811 0.00886 -0.0756 0.8451 0.3036
-2.750 -0.0210 0.01805 0.00872 -0.0752 0.8367 0.3180
-2.500 0.0180 0.01787 0.00845 -0.0773 0.8320 0.3337
-2.250 0.0415 0.01787 0.00839 -0.0763 0.8227 0.3465
-2.000 0.0772 0.01774 0.00818 -0.0777 0.8173 0.3601
-1.750 0.1027 0.01771 0.00810 -0.0771 0.8090 0.3708
-1.500 0.1355 0.01760 0.00789 -0.0779 0.8023 0.3826
-1.250 0.1630 0.01755 0.00777 -0.0778 0.7943 0.3932
-1.000 0.1934 0.01744 0.00763 -0.0781 0.7868 0.4025
-0.750 0.2207 0.01738 0.00751 -0.0779 0.7784 0.4122
-0.500 0.2510 0.01726 0.00736 -0.0782 0.7703 0.4219
-0.250 0.2762 0.01721 0.00730 -0.0776 0.7620 0.4304
0.000 0.3063 0.01713 0.00718 -0.0780 0.7548 0.4400
0.250 0.3319 0.01707 0.00716 -0.0774 0.7469 0.4485
0.500 0.3618 0.01699 0.00709 -0.0778 0.7395 0.4598
0.750 0.3886 0.01696 0.00707 -0.0775 0.7311 0.4717
1.000 0.4221 0.01683 0.00699 -0.0786 0.7234 0.4845
1.250 0.4500 0.01678 0.00701 -0.0786 0.7141 0.4967
1.500 0.4855 0.01663 0.00690 -0.0800 0.7066 0.5099
1.750 0.5111 0.01661 0.00697 -0.0796 0.6968 0.5226
2.000 0.5421 0.01651 0.00693 -0.0801 0.6884 0.5366
2.250 0.5698 0.01641 0.00697 -0.0800 0.6786 0.5559
3.250 0.7932 0.01613 0.00768 -0.1035 0.6324 1.0000
3.500 0.8156 0.01632 0.00784 -0.1023 0.6206 1.0000
3.750 0.8393 0.01652 0.00800 -0.1014 0.6094 1.0000
4.000 0.8612 0.01674 0.00819 -0.1000 0.5974 1.0000
4.250 0.8806 0.01698 0.00846 -0.0983 0.5846 1.0000
4.500 0.9008 0.01723 0.00871 -0.0967 0.5722 1.0000
4.750 0.9216 0.01747 0.00897 -0.0952 0.5605 1.0000
5.000 0.9421 0.01771 0.00921 -0.0936 0.5489 1.0000
5.250 0.9605 0.01798 0.00953 -0.0917 0.5366 1.0000
5.500 0.9796 0.01825 0.00984 -0.0899 0.5250 1.0000
5.750 0.9986 0.01851 0.01012 -0.0880 0.5134 1.0000
6.000 1.0174 0.01877 0.01037 -0.0861 0.5014 1.0000
6.250 1.0355 0.01905 0.01066 -0.0841 0.4895 1.0000
6.500 1.0534 0.01937 0.01100 -0.0821 0.4782 1.0000
6.750 1.0726 0.01971 0.01139 -0.0804 0.4684 1.0000
7.000 1.0923 0.02008 0.01176 -0.0788 0.4590 1.0000
7.250 1.1103 0.02049 0.01225 -0.0769 0.4494 1.0000
7.500 1.1280 0.02091 0.01268 -0.0749 0.4380 1.0000
7.750 1.1386 0.02137 0.01311 -0.0716 0.4199 1.0000
8.000 1.1441 0.02187 0.01357 -0.0673 0.3980 1.0000
8.250 1.1453 0.02236 0.01400 -0.0623 0.3763 1.0000
8.500 1.1444 0.02281 0.01451 -0.0570 0.3540 1.0000
8.750 1.1446 0.02335 0.01504 -0.0522 0.3282 1.0000
9.000 1.1457 0.02400 0.01567 -0.0477 0.2953 1.0000
9.250 1.1433 0.02494 0.01642 -0.0431 0.2559 1.0000
9.500 1.1362 0.02634 0.01751 -0.0382 0.2112 1.0000
9.750 1.1293 0.02803 0.01893 -0.0338 0.1693 1.0000
10.000 1.1220 0.02998 0.02062 -0.0298 0.1268 1.0000
10.250 1.1124 0.03225 0.02262 -0.0260 0.0882 1.0000
10.500 1.1048 0.03451 0.02475 -0.0228 0.0658 1.0000
10.750 1.0996 0.03674 0.02693 -0.0200 0.0539 1.0000
11.000 1.0957 0.03899 0.02919 -0.0176 0.0472 1.0000
11.250 1.0929 0.04125 0.03150 -0.0156 0.0431 1.0000
11.500 1.0890 0.04372 0.03401 -0.0138 0.0409 1.0000
11.750 1.0872 0.04611 0.03656 -0.0122 0.0385 1.0000
12.000 1.0854 0.04860 0.03917 -0.0109 0.0367 1.0000
12.250 1.0831 0.05122 0.04189 -0.0098 0.0351 1.0000
12.500 1.0793 0.05407 0.04482 -0.0088 0.0339 1.0000
12.750 1.0751 0.05703 0.04786 -0.0080 0.0323 1.0000
13.000 1.0755 0.05960 0.05056 -0.0072 0.0312 1.0000
13.250 1.0756 0.06224 0.05334 -0.0066 0.0300 1.0000
13.500 1.0766 0.06479 0.05599 -0.0059 0.0292 1.0000
13.750 1.0783 0.06730 0.05857 -0.0052 0.0284 1.0000
14.000 1.0806 0.06976 0.06107 -0.0046 0.0275 1.0000
14.250 1.0845 0.07199 0.06333 -0.0038 0.0268 1.0000
14.500 1.0917 0.07382 0.06514 -0.0027 0.0260 1.0000
14.750 1.0964 0.07622 0.06773 -0.0022 0.0251 1.0000
15.000 1.1004 0.07876 0.07043 -0.0019 0.0241 1.0000
15.250 1.1051 0.08121 0.07302 -0.0014 0.0234 1.0000
15.500 1.1096 0.08373 0.07571 -0.0010 0.0230 1.0000
15.750 1.1125 0.08651 0.07863 -0.0008 0.0225 1.0000
16.000 1.1143 0.08952 0.08179 -0.0008 0.0221 1.0000
16.250 1.1143 0.09282 0.08524 -0.0010 0.0218 1.0000
16.500 1.1128 0.09637 0.08895 -0.0015 0.0215 1.0000
16.750 1.1097 0.10021 0.09295 -0.0023 0.0213 1.0000
17.000 1.1052 0.10433 0.09722 -0.0033 0.0210 1.0000
17.250 1.0996 0.10873 0.10176 -0.0046 0.0208 1.0000
17.500 1.0925 0.11344 0.10664 -0.0063 0.0206 1.0000
18.000 1.0739 0.12398 0.11745 -0.0108 0.0202 1.0000
18.250 1.0565 0.13120 0.12491 -0.0148 0.0201 1.0000
18.500 1.0422 0.13807 0.13197 -0.0186 0.0202 1.0000
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Polar data table (+)
Polar graphs
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