NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il) Reynolds number: 200,000 Max Cl/Cd: 56.43 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls421-il-200000-n5.txt Download as CSV file: xf-ls421-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0421 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
------ -------- --------- --------- -------- -------- --------
-19.750 -0.7893 0.12202 0.11656 -0.0611 1.0000 0.0321
-19.500 -0.8040 0.11525 0.10966 -0.0652 1.0000 0.0323
-19.250 -0.8156 0.10921 0.10351 -0.0688 1.0000 0.0325
-19.000 -0.8252 0.10367 0.09784 -0.0720 1.0000 0.0327
-18.750 -0.8335 0.09845 0.09251 -0.0749 1.0000 0.0329
-18.500 -0.8409 0.09349 0.08743 -0.0777 1.0000 0.0331
-18.250 -0.8469 0.08884 0.08267 -0.0802 1.0000 0.0334
-18.000 -0.8518 0.08447 0.07818 -0.0825 1.0000 0.0337
-17.750 -0.8556 0.08036 0.07395 -0.0846 1.0000 0.0340
-17.500 -0.8585 0.07647 0.06993 -0.0865 1.0000 0.0344
-17.250 -0.8603 0.07281 0.06615 -0.0882 1.0000 0.0348
-17.000 -0.8614 0.06935 0.06255 -0.0897 1.0000 0.0353
-16.750 -0.8616 0.06611 0.05915 -0.0910 1.0000 0.0358
-16.500 -0.8590 0.06334 0.05626 -0.0920 1.0000 0.0362
-16.250 -0.8526 0.06118 0.05412 -0.0927 1.0000 0.0366
-16.000 -0.8447 0.05900 0.05190 -0.0940 0.9879 0.0371
-15.750 -0.8339 0.05670 0.04954 -0.0958 0.9753 0.0376
-15.500 -0.8228 0.05449 0.04724 -0.0973 0.9644 0.0382
-15.250 -0.8127 0.05243 0.04508 -0.0983 0.9538 0.0388
-15.000 -0.8027 0.05054 0.04307 -0.0989 0.9446 0.0395
-14.750 -0.7936 0.04877 0.04117 -0.0990 0.9354 0.0401
-14.500 -0.7840 0.04715 0.03945 -0.0989 0.9279 0.0407
-14.250 -0.7748 0.04559 0.03786 -0.0987 0.9202 0.0413
-14.000 -0.7654 0.04410 0.03633 -0.0985 0.9133 0.0419
-13.750 -0.7556 0.04268 0.03484 -0.0981 0.9074 0.0427
-13.500 -0.7450 0.04131 0.03340 -0.0979 0.9009 0.0436
-13.250 -0.7339 0.04006 0.03204 -0.0974 0.8948 0.0446
-13.000 -0.7233 0.03882 0.03072 -0.0967 0.8896 0.0455
-12.750 -0.7123 0.03754 0.02942 -0.0964 0.8843 0.0464
-12.500 -0.6999 0.03637 0.02822 -0.0961 0.8791 0.0474
-12.250 -0.6874 0.03526 0.02704 -0.0956 0.8744 0.0486
-12.000 -0.6743 0.03422 0.02591 -0.0950 0.8703 0.0498
-11.750 -0.6617 0.03314 0.02479 -0.0945 0.8664 0.0510
-11.500 -0.6481 0.03208 0.02373 -0.0942 0.8620 0.0523
-11.250 -0.6336 0.03113 0.02273 -0.0938 0.8575 0.0539
-11.000 -0.6185 0.03025 0.02177 -0.0932 0.8532 0.0557
-10.750 -0.6054 0.02926 0.02077 -0.0926 0.8494 0.0573
-10.500 -0.5908 0.02839 0.01985 -0.0919 0.8461 0.0592
-10.250 -0.5739 0.02761 0.01903 -0.0916 0.8423 0.0616
-10.000 -0.5591 0.02672 0.01817 -0.0911 0.8385 0.0639
-9.750 -0.5425 0.02597 0.01738 -0.0906 0.8348 0.0669
-9.500 -0.5268 0.02518 0.01659 -0.0900 0.8315 0.0700
-9.250 -0.5103 0.02445 0.01583 -0.0894 0.8284 0.0739
-9.000 -0.4943 0.02371 0.01508 -0.0887 0.8256 0.0783
-8.750 -0.4778 0.02305 0.01442 -0.0880 0.8222 0.0838
-8.500 -0.4627 0.02243 0.01383 -0.0871 0.8183 0.0903
-8.250 -0.4493 0.02184 0.01327 -0.0858 0.8147 0.0976
-8.000 -0.4333 0.02125 0.01270 -0.0850 0.8116 0.1066
-7.750 -0.4150 0.02066 0.01214 -0.0846 0.8088 0.1178
-7.500 -0.3952 0.02008 0.01159 -0.0844 0.8064 0.1311
-7.250 -0.3744 0.01948 0.01105 -0.0844 0.8042 0.1468
-7.000 -0.3529 0.01893 0.01059 -0.0845 0.8015 0.1658
-6.500 -0.3082 0.01787 0.00978 -0.0850 0.7950 0.2151
-6.250 -0.2842 0.01730 0.00937 -0.0855 0.7922 0.2487
-6.000 -0.2587 0.01674 0.00898 -0.0862 0.7898 0.2877
-5.750 -0.2317 0.01622 0.00862 -0.0871 0.7876 0.3274
-5.500 -0.2036 0.01568 0.00828 -0.0881 0.7856 0.3730
-5.250 -0.1746 0.01515 0.00803 -0.0892 0.7838 0.4299
-5.000 -0.1454 0.01485 0.00803 -0.0899 0.7820 0.4885
-4.750 -0.1178 0.01494 0.00835 -0.0899 0.7791 0.5311
-4.500 -0.0886 0.01507 0.00853 -0.0903 0.7763 0.5589
-4.250 -0.0589 0.01521 0.00869 -0.0907 0.7738 0.5791
-4.000 -0.0291 0.01538 0.00885 -0.0911 0.7714 0.5951
-3.750 0.0002 0.01559 0.00905 -0.0913 0.7691 0.6071
-3.500 0.0318 0.01565 0.00903 -0.0922 0.7668 0.6195
-3.250 0.0608 0.01587 0.00926 -0.0921 0.7647 0.6277
-3.000 0.0935 0.01593 0.00922 -0.0932 0.7629 0.6389
-2.750 0.1214 0.01625 0.00954 -0.0927 0.7613 0.6447
-2.500 0.1496 0.01647 0.00978 -0.0928 0.7587 0.6508
-2.250 0.1806 0.01650 0.00975 -0.0941 0.7555 0.6577
-2.000 0.2082 0.01667 0.00993 -0.0940 0.7525 0.6611
-1.750 0.2357 0.01684 0.01011 -0.0939 0.7497 0.6641
-1.500 0.2646 0.01695 0.01022 -0.0940 0.7472 0.6677
-1.250 0.2952 0.01700 0.01023 -0.0946 0.7449 0.6719
-1.000 0.3284 0.01695 0.01011 -0.0959 0.7429 0.6776
-0.750 0.3595 0.01698 0.01010 -0.0965 0.7409 0.6816
-0.500 0.3845 0.01724 0.01042 -0.0959 0.7375 0.6845
-0.250 0.4096 0.01746 0.01070 -0.0954 0.7332 0.6876
0.000 0.4377 0.01753 0.01078 -0.0955 0.7294 0.6908
0.250 0.4687 0.01747 0.01070 -0.0962 0.7258 0.6943
0.500 0.5026 0.01731 0.01048 -0.0976 0.7227 0.6981
0.750 0.5381 0.01711 0.01020 -0.0993 0.7198 0.7016
1.000 0.5599 0.01728 0.01047 -0.0983 0.7130 0.7033
1.250 0.5873 0.01723 0.01044 -0.0980 0.7071 0.7051
1.500 0.6183 0.01707 0.01026 -0.0984 0.7024 0.7070
1.750 0.6470 0.01702 0.01022 -0.0986 0.6972 0.7089
2.000 0.6723 0.01708 0.01033 -0.0983 0.6900 0.7111
2.250 0.7030 0.01689 0.01012 -0.0988 0.6831 0.7136
2.500 0.7309 0.01681 0.01005 -0.0989 0.6742 0.7162
2.750 0.7600 0.01668 0.00991 -0.0993 0.6647 0.7187
3.000 0.7896 0.01660 0.00981 -0.0999 0.6558 0.7211
3.250 0.8174 0.01656 0.00977 -0.1001 0.6456 0.7235
3.500 0.8416 0.01658 0.00984 -0.0994 0.6349 0.7251
3.750 0.8674 0.01655 0.00979 -0.0989 0.6228 0.7266
4.000 0.8898 0.01663 0.00990 -0.0980 0.6076 0.7283
4.250 0.9132 0.01668 0.00994 -0.0971 0.5896 0.7300
4.500 0.9360 0.01676 0.00993 -0.0962 0.5669 0.7319
4.750 0.9559 0.01694 0.00999 -0.0948 0.5379 0.7339
5.000 0.9710 0.01730 0.01015 -0.0926 0.5045 0.7364
5.250 0.9785 0.01784 0.01049 -0.0892 0.4715 0.7393
5.500 0.9841 0.01853 0.01100 -0.0858 0.4404 0.7421
6.000 1.0001 0.02038 0.01254 -0.0805 0.3821 0.7461
6.250 1.0077 0.02139 0.01345 -0.0779 0.3565 0.7478
6.500 1.0156 0.02246 0.01441 -0.0756 0.3329 0.7496
7.000 1.0348 0.02461 0.01637 -0.0717 0.2916 0.7536
7.250 1.0456 0.02570 0.01739 -0.0701 0.2733 0.7559
7.500 1.0576 0.02676 0.01839 -0.0687 0.2564 0.7585
7.750 1.0704 0.02783 0.01939 -0.0675 0.2409 0.7612
8.000 1.0840 0.02889 0.02039 -0.0665 0.2270 0.7637
8.250 1.0975 0.03001 0.02145 -0.0655 0.2145 0.7659
8.750 1.1218 0.03216 0.02357 -0.0629 0.1933 0.7693
9.000 1.1338 0.03329 0.02468 -0.0617 0.1847 0.7712
9.250 1.1468 0.03437 0.02577 -0.0606 0.1765 0.7733
9.500 1.1591 0.03554 0.02692 -0.0595 0.1694 0.7755
9.750 1.1726 0.03665 0.02805 -0.0586 0.1627 0.7778
10.000 1.1848 0.03790 0.02928 -0.0577 0.1569 0.7803
10.250 1.1992 0.03903 0.03044 -0.0570 0.1512 0.7830
10.500 1.2114 0.04037 0.03175 -0.0563 0.1461 0.7858
10.750 1.2246 0.04153 0.03295 -0.0554 0.1417 0.7880
11.000 1.2368 0.04276 0.03424 -0.0545 0.1371 0.7901
11.250 1.2471 0.04419 0.03567 -0.0535 0.1333 0.7924
11.500 1.2605 0.04541 0.03696 -0.0528 0.1296 0.7948
11.750 1.2729 0.04675 0.03834 -0.0521 0.1259 0.7973
12.000 1.2836 0.04827 0.03987 -0.0514 0.1227 0.7999
12.250 1.2954 0.04973 0.04136 -0.0508 0.1198 0.8027
12.500 1.3085 0.05114 0.04283 -0.0503 0.1167 0.8054
12.750 1.3191 0.05269 0.04443 -0.0497 0.1138 0.8077
13.000 1.3277 0.05439 0.04615 -0.0489 0.1113 0.8099
13.250 1.3385 0.05593 0.04777 -0.0483 0.1089 0.8126
13.500 1.3493 0.05750 0.04943 -0.0477 0.1064 0.8156
13.750 1.3590 0.05922 0.05121 -0.0472 0.1040 0.8189
14.000 1.3671 0.06117 0.05318 -0.0468 0.1020 0.8221
14.250 1.3764 0.06304 0.05509 -0.0465 0.1000 0.8253
14.500 1.3860 0.06476 0.05692 -0.0460 0.0978 0.8278
14.750 1.3940 0.06668 0.05893 -0.0456 0.0957 0.8305
15.000 1.4008 0.06875 0.06106 -0.0452 0.0939 0.8335
15.250 1.4066 0.07098 0.06331 -0.0449 0.0924 0.8366
15.500 1.4148 0.07303 0.06546 -0.0447 0.0906 0.8400
15.750 1.4228 0.07515 0.06768 -0.0446 0.0888 0.8433
16.000 1.4285 0.07742 0.07005 -0.0444 0.0871 0.8462
16.250 1.4331 0.07982 0.07251 -0.0443 0.0856 0.8494
16.500 1.4370 0.08234 0.07506 -0.0442 0.0843 0.8530
16.750 1.4423 0.08476 0.07758 -0.0443 0.0828 0.8570
17.000 1.4477 0.08727 0.08021 -0.0445 0.0813 0.8611
17.250 1.4511 0.08986 0.08292 -0.0445 0.0799 0.8648
17.500 1.4542 0.09256 0.08571 -0.0447 0.0786 0.8690
17.750 1.4567 0.09541 0.08862 -0.0451 0.0774 0.8734
18.000 1.4596 0.09819 0.09141 -0.0456 0.0763 0.8778
18.250 1.4614 0.10111 0.09449 -0.0460 0.0751 0.8820
18.500 1.4629 0.10409 0.09762 -0.0466 0.0738 0.8869
18.750 1.4642 0.10721 0.10085 -0.0474 0.0726 0.8922
19.000 1.4648 0.11033 0.10407 -0.0481 0.0716 0.8977
19.250 1.4652 0.11347 0.10729 -0.0490 0.0706 0.9044
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)