NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.78 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413mod-il-1000000.txt Download as CSV file: xf-ls413mod-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413MOD AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4283 0.08696 0.08528 -0.0455 1.0000 0.0248
-12.000 -0.4387 0.08050 0.07883 -0.0478 1.0000 0.0250
-11.750 -0.7486 0.04509 0.04251 -0.0696 1.0000 0.0195
-11.500 -0.7742 0.04207 0.03939 -0.0671 1.0000 0.0193
-11.250 -0.7934 0.03893 0.03607 -0.0646 1.0000 0.0191
-11.000 -0.8000 0.03507 0.03192 -0.0638 0.9990 0.0189
-10.750 -0.7818 0.03075 0.02723 -0.0670 0.9963 0.0187
-10.500 -0.7570 0.02769 0.02385 -0.0696 0.9944 0.0188
-10.250 -0.7298 0.02541 0.02132 -0.0716 0.9924 0.0189
-10.000 -0.7025 0.02317 0.01884 -0.0733 0.9896 0.0188
-9.750 -0.6726 0.02120 0.01666 -0.0751 0.9874 0.0188
-9.500 -0.6409 0.01963 0.01492 -0.0769 0.9855 0.0188
-9.250 -0.6083 0.01837 0.01352 -0.0786 0.9837 0.0189
-9.000 -0.5772 0.01732 0.01237 -0.0799 0.9804 0.0191
-8.750 -0.5475 0.01645 0.01141 -0.0807 0.9751 0.0193
-8.500 -0.5160 0.01566 0.01055 -0.0819 0.9707 0.0195
-8.250 -0.4876 0.01501 0.00983 -0.0823 0.9631 0.0197
-8.000 -0.4584 0.01443 0.00919 -0.0828 0.9560 0.0199
-7.750 -0.4309 0.01397 0.00867 -0.0829 0.9465 0.0200
-7.500 -0.4036 0.01335 0.00798 -0.0830 0.9376 0.0202
-7.250 -0.3771 0.01236 0.00694 -0.0831 0.9276 0.0205
-7.000 -0.3493 0.01173 0.00627 -0.0835 0.9181 0.0209
-6.500 -0.2922 0.01092 0.00538 -0.0841 0.8993 0.0217
-6.250 -0.2632 0.01060 0.00501 -0.0845 0.8904 0.0222
-6.000 -0.2338 0.01029 0.00466 -0.0850 0.8812 0.0228
-5.750 -0.2043 0.01002 0.00434 -0.0854 0.8726 0.0234
-5.500 -0.1747 0.00981 0.00409 -0.0858 0.8636 0.0241
-5.250 -0.1444 0.00945 0.00366 -0.0865 0.8552 0.0252
-5.000 -0.1142 0.00916 0.00334 -0.0871 0.8460 0.0265
-4.750 -0.0840 0.00895 0.00310 -0.0876 0.8370 0.0278
-4.500 -0.0540 0.00880 0.00288 -0.0880 0.8276 0.0291
-4.250 -0.0232 0.00855 0.00263 -0.0887 0.8190 0.0325
-4.000 0.0073 0.00837 0.00244 -0.0893 0.8109 0.0390
-3.750 0.0388 0.00807 0.00227 -0.0903 0.8033 0.0692
-3.500 0.0710 0.00765 0.00210 -0.0916 0.7958 0.1366
-3.250 0.1043 0.00716 0.00193 -0.0932 0.7884 0.2338
-3.000 0.1383 0.00663 0.00179 -0.0951 0.7803 0.3495
-2.750 0.1722 0.00620 0.00167 -0.0968 0.7729 0.4575
-2.500 0.2056 0.00586 0.00163 -0.0983 0.7649 0.5553
-2.250 0.2369 0.00578 0.00165 -0.0990 0.7566 0.6067
-2.000 0.2671 0.00579 0.00167 -0.0994 0.7460 0.6369
-1.750 0.2971 0.00582 0.00168 -0.0997 0.7338 0.6521
-1.500 0.3269 0.00587 0.00169 -0.1000 0.7221 0.6652
-1.000 0.3864 0.00598 0.00178 -0.1005 0.7022 0.6906
-0.750 0.4160 0.00605 0.00180 -0.1008 0.6913 0.6988
-0.500 0.4453 0.00613 0.00183 -0.1009 0.6782 0.7051
-0.250 0.4748 0.00623 0.00187 -0.1012 0.6631 0.7123
0.000 0.5040 0.00629 0.00191 -0.1013 0.6480 0.7188
0.250 0.5333 0.00637 0.00195 -0.1016 0.6331 0.7231
0.500 0.5627 0.00647 0.00198 -0.1018 0.6176 0.7265
0.750 0.5921 0.00657 0.00202 -0.1021 0.6029 0.7295
1.000 0.6212 0.00666 0.00207 -0.1023 0.5854 0.7330
1.250 0.6498 0.00680 0.00214 -0.1024 0.5643 0.7367
1.500 0.6786 0.00695 0.00222 -0.1026 0.5424 0.7409
1.750 0.7070 0.00716 0.00231 -0.1027 0.5164 0.7450
2.250 0.7626 0.00766 0.00256 -0.1028 0.4502 0.7525
2.500 0.7903 0.00794 0.00270 -0.1028 0.4185 0.7557
2.750 0.8182 0.00820 0.00285 -0.1029 0.3900 0.7587
3.000 0.8458 0.00849 0.00301 -0.1030 0.3596 0.7616
3.250 0.8729 0.00884 0.00319 -0.1030 0.3245 0.7644
3.500 0.8996 0.00918 0.00341 -0.1029 0.2918 0.7677
3.750 0.9264 0.00951 0.00362 -0.1028 0.2643 0.7709
4.000 0.9533 0.00984 0.00385 -0.1027 0.2407 0.7742
4.250 0.9803 0.01016 0.00407 -0.1026 0.2187 0.7777
4.500 1.0069 0.01050 0.00430 -0.1026 0.1985 0.7811
4.750 1.0333 0.01081 0.00455 -0.1024 0.1798 0.7847
5.000 1.0598 0.01113 0.00480 -0.1022 0.1637 0.7882
5.250 1.0862 0.01145 0.00506 -0.1021 0.1504 0.7917
5.500 1.1129 0.01174 0.00531 -0.1020 0.1410 0.7954
5.750 1.1393 0.01201 0.00557 -0.1018 0.1331 0.7990
6.000 1.1652 0.01232 0.00585 -0.1015 0.1252 0.8026
6.250 1.1915 0.01259 0.00612 -0.1013 0.1183 0.8064
6.500 1.2172 0.01292 0.00641 -0.1011 0.1108 0.8103
6.750 1.2433 0.01319 0.00669 -0.1009 0.1057 0.8140
7.000 1.2688 0.01346 0.00698 -0.1005 0.1012 0.8180
7.250 1.2934 0.01384 0.00734 -0.1001 0.0954 0.8222
7.500 1.3194 0.01409 0.00762 -0.0998 0.0928 0.8265
7.750 1.3445 0.01439 0.00792 -0.0995 0.0890 0.8304
8.000 1.3681 0.01478 0.00830 -0.0988 0.0838 0.8344
8.250 1.3930 0.01506 0.00863 -0.0984 0.0815 0.8387
8.500 1.4176 0.01537 0.00896 -0.0980 0.0789 0.8433
8.750 1.4410 0.01573 0.00933 -0.0973 0.0758 0.8476
9.000 1.4632 0.01617 0.00978 -0.0965 0.0720 0.8520
9.250 1.4871 0.01646 0.01013 -0.0959 0.0703 0.8566
9.500 1.5103 0.01681 0.01050 -0.0953 0.0679 0.8609
9.750 1.5317 0.01721 0.01092 -0.0943 0.0647 0.8654
10.000 1.5523 0.01769 0.01142 -0.0932 0.0611 0.8704
10.250 1.5745 0.01804 0.01181 -0.0925 0.0585 0.8753
10.500 1.5930 0.01856 0.01232 -0.0911 0.0535 0.8801
10.750 1.6117 0.01906 0.01284 -0.0897 0.0479 0.8852
11.000 1.6260 0.01981 0.01353 -0.0878 0.0394 0.8905
11.250 1.6357 0.02061 0.01431 -0.0849 0.0337 0.8963
11.500 1.6448 0.02143 0.01516 -0.0821 0.0305 0.9028
11.750 1.6557 0.02224 0.01601 -0.0797 0.0287 0.9093
12.000 1.6648 0.02319 0.01703 -0.0771 0.0271 0.9169
12.250 1.6742 0.02415 0.01806 -0.0747 0.0259 0.9255
12.500 1.6851 0.02498 0.01898 -0.0727 0.0253 0.9365
12.750 1.6920 0.02581 0.01993 -0.0699 0.0246 0.9633
13.000 1.7011 0.02694 0.02112 -0.0681 0.0238 1.0000
13.250 1.7099 0.02828 0.02252 -0.0665 0.0230 1.0000
13.500 1.7162 0.02988 0.02418 -0.0648 0.0221 1.0000
13.750 1.7223 0.03154 0.02591 -0.0632 0.0215 1.0000
14.000 1.7321 0.03292 0.02737 -0.0621 0.0212 1.0000
14.250 1.7410 0.03441 0.02894 -0.0610 0.0208 1.0000
14.500 1.7482 0.03610 0.03070 -0.0600 0.0203 1.0000
14.750 1.7538 0.03796 0.03265 -0.0589 0.0199 1.0000
15.000 1.7579 0.04004 0.03480 -0.0580 0.0195 1.0000
15.250 1.7604 0.04234 0.03718 -0.0572 0.0191 1.0000
15.500 1.7604 0.04495 0.03986 -0.0564 0.0187 1.0000
15.750 1.7579 0.04792 0.04293 -0.0558 0.0183 1.0000
16.000 1.7518 0.05144 0.04656 -0.0554 0.0180 1.0000
16.250 1.7453 0.05514 0.05036 -0.0553 0.0177 1.0000
16.500 1.7453 0.05816 0.05348 -0.0554 0.0175 1.0000
16.750 1.7436 0.06149 0.05692 -0.0556 0.0174 1.0000
17.000 1.7400 0.06517 0.06071 -0.0561 0.0172 1.0000
17.250 1.7345 0.06922 0.06487 -0.0568 0.0170 1.0000
17.500 1.7271 0.07362 0.06939 -0.0577 0.0167 1.0000
17.750 1.7176 0.07847 0.07435 -0.0590 0.0166 1.0000
18.000 1.7067 0.08365 0.07966 -0.0605 0.0164 1.0000
18.250 1.6931 0.08934 0.08547 -0.0624 0.0162 1.0000
18.500 1.6774 0.09547 0.09172 -0.0646 0.0160 1.0000
18.750 1.6598 0.10207 0.09845 -0.0671 0.0159 1.0000
19.000 1.6397 0.10920 0.10572 -0.0701 0.0158 1.0000
19.250 1.6171 0.11688 0.11354 -0.0735 0.0157 1.0000
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Polar data table (+)
Polar graphs
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