NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il)
NASA/LANGLEY LS(1)-0421MOD AIRFOIL - NASA/Langley LS(1)-0421MOD general aviation airfoil
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(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD AIRFOIL NASA/Langley LS(1)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord. Max camber 2.3% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY LS(1)-0421MOD AIRFOIL 45. 45. 0.00000 0.00000 .00200 .01560 .00500 .02430 .01250 .03830 .02500 .05400 .03750 .06510 .05000 .07360 .07500 .08650 .10000 .09600 .12500 .10340 .15000 .10930 .17500 .11410 .20000 .11790 .22500 .12080 .25000 .12290 .27500 .12430 .30000 .12500 .32500 .12500 .35000 .12440 .37500 .12330 .40000 .12170 .42500 .11960 .45000 .11700 .47500 .11400 .50000 .11060 .52500 .10680 .55000 .10270 .57500 .09830 .60000 .09360 .62500 .08860 .65000 .08330 .67500 .07780 .70000 .07210 .72500 .06620 .75000 .06010 .77500 .05390 .80000 .04760 .82500 .04120 .85000 .03480 .87500 .02840 .90000 .02200 .92500 .01560 .95000 .00910 .97500 .00250 1.00000 -.00420 0.00000 0.00000 .00200 -.01070 .00500 -.01770 .01250 -.02650 .02500 -.03520 .03750 -.04160 .05000 -.04680 .07500 -.05500 .10000 -.06140 .12500 -.06650 .15000 -.07070 .17500 -.07410 .20000 -.07700 .22500 -.07940 .25000 -.08130 .27500 -.08280 .30000 -.08390 .32500 -.08460 .35000 -.08490 .37500 -.08490 .40000 -.08460 .42500 -.08390 .45000 -.08280 .47500 -.08130 .50000 -.07940 .52500 -.07700 .55000 -.07400 .57500 -.07050 .60000 -.06660 .62500 -.06230 .65000 -.05760 .67500 -.05250 .70000 -.04720 .72500 -.04180 .75000 -.03640 .77500 -.03100 .80000 -.02560 .82500 -.02060 .85000 -.01590 .87500 -.01180 .90000 -.00860 .92500 -.00700 .95000 -.00690 .97500 -.00880 1.00000 -.01320 |
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Polars for NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ls421mod-il | 50,000 | 9 | 7.2 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 50,000 | 5 | 18.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 100,000 | 9 | 37.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 100,000 | 5 | 38.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 200,000 | 9 | 51.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 200,000 | 5 | 56 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 500,000 | 9 | 80.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 500,000 | 5 | 77.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421mod-il | 1,000,000 | 9 | 100 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421mod-il | 1,000,000 | 5 | 90.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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