NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)
NASA/LANGLEY LS(1)-0421 AIRFOIL - NASA/Langley LS(1)-0421 general aviation airfoil
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(ls421-il) NASA/LANGLEY LS(1)-0421 AIRFOIL NASA/Langley LS(1)-0421 general aviation airfoil Max thickness 20.9% at 40% chord. Max camber 2.4% at 65% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY LS(1)-0421 AIRFOIL 38. 38. 0.00000 0.00000 .00200 .01560 .00500 .02377 .01250 .03599 .02500 .04912 .03750 .05853 .05000 .06606 .07500 .07771 .10000 .08664 .12500 .09388 .15000 .09993 .17500 .10507 .20000 .10943 .25000 .11617 .30000 .12074 .35000 .12344 .40000 .12439 .45000 .12365 .50000 .12112 .55000 .11657 .57500 .11342 .60000 .10965 .62500 .10525 .65000 .10025 .67500 .09470 .70000 .08865 .72500 .08216 .75000 .07530 .77500 .06814 .80000 .06075 .82500 .05318 .85000 .04550 .87500 .03775 .90000 .03000 .92500 .02232 .95000 .01476 .97500 .00735 1.00000 .00016 0.00000 0.00000 .00200 -.01071 .00500 -.01775 .01250 -.02653 .02500 -.03522 .03750 -.04137 .05000 -.04650 .07500 -.05463 .10000 -.06097 .12500 -.06612 .15000 -.07038 .17500 -.07393 .20000 -.07690 .25000 -.08130 .30000 -.08381 .35000 -.08484 .40000 -.08455 .45000 -.08288 .50000 -.07970 .55000 -.07452 .57500 -.07104 .60000 -.06701 .62500 -.06247 .65000 -.05752 .67500 -.05226 .70000 -.04678 .72500 -.04117 .75000 -.03553 .77500 -.02994 .80000 -.02456 .82500 -.01953 .85000 -.01500 .87500 -.01112 .90000 -.00805 .92500 -.00598 .95000 -.00515 .97500 -.00589 1.00000 -.00886 |
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Polars for NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ls421-il | 50,000 | 9 | 23.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 50,000 | 5 | 18.4 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 100,000 | 9 | 33.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 100,000 | 5 | 30.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 200,000 | 9 | 52.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 200,000 | 5 | 56.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 500,000 | 9 | 89.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 500,000 | 5 | 81.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls421-il | 1,000,000 | 9 | 111.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls421-il | 1,000,000 | 5 | 91.2 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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