NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il)
NASA/LANGLEY LS(1)-0413MOD AIRFOIL - NASA/Langley LS(1)-0413MOD general aviation airfoil
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(ls413mod-il) NASA/LANGLEY LS(1)-0413MOD AIRFOIL NASA/Langley LS(1)-0413MOD general aviation airfoil Max thickness 13% at 35% chord. Max camber 2.2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY LS(1)-0413MOD AIRFOIL 45. 44. 0.00000 0.00000 .00200 .01040 .00500 .01590 .01250 .02440 .02500 .03420 .03750 .04180 .05000 .04760 .07500 .05640 .10000 .06290 .12500 .06800 .15000 .07220 .17500 .07560 .20000 .07830 .22500 .08050 .25000 .08220 .27500 .08350 .30000 .08440 .32500 .08490 .35000 .08500 .37500 .08470 .40000 .08410 .42500 .08320 .45000 .08200 .47500 .08050 .50000 .07870 .52500 .07660 .55000 .07420 .57500 .07150 .60000 .06850 .62500 .06530 .65000 .06180 .67500 .05810 .70000 .05420 .72500 .05010 .75000 .04580 .77500 .04140 .80000 .03680 .82500 .03210 .85000 .02730 .87500 .02240 .90000 .01740 .92500 .01230 .95000 .00700 .97500 .00150 1.00000 -.00430 0.00000 0.00000 .00200 -.00500 .00500 -.00940 .01250 -.01450 .02500 -.01910 .03750 -.02280 .05000 -.02550 .07500 -.02990 .10000 -.03330 .12500 -.03600 .15000 -.03820 .17500 -.04000 .20000 -.04150 .22500 -.04270 .25000 -.04360 .27500 -.04430 .30000 -.04480 .32500 -.04510 .35000 -.04520 .37500 -.04500 .40000 -.04470 .42500 -.04420 .45000 -.04350 .47500 -.04260 .50000 -.04150 .52500 -.04010 .55000 -.03850 .57500 -.03660 .60000 -.03440 .62500 -.03190 .65000 -.02910 .67500 -.02620 .70000 -.02320 .72500 -.02020 .75000 -.01720 .77500 -.01420 .80000 -.01120 .82500 -.00840 .87500 -.00390 .90000 -.00260 .92500 -.00210 .95000 -.00280 .97500 -.00510 1.00000 -.00940 |
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Polars for NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ls413mod-il | 50,000 | 9 | 34.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 50,000 | 5 | 35.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 100,000 | 9 | 53.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 100,000 | 5 | 49.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 200,000 | 9 | 66 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 200,000 | 5 | 62 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 500,000 | 9 | 86.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 500,000 | 5 | 77.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 1,000,000 | 9 | 99.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 1,000,000 | 5 | 92.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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