NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il)
NASA/LANGLEY LS(1)-0417MOD AIRFOIL - NASA/Langley LS(1)-0417MOD general aviation airfoil
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(ls417mod-il) NASA/LANGLEY LS(1)-0417MOD AIRFOIL NASA/Langley LS(1)-0417MOD general aviation airfoil Max thickness 17% at 30.2% chord. Max camber 2.3% at 20.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY LS(1)-0417MOD AIRFOIL 46. 47. 0.00000 0.00000 .00124 .01286 .00239 .01665 .00741 .02642 .01300 .03408 .02088 .04266 .03133 .05170 .04150 .05894 .05080 .06464 .07102 .07488 .09992 .08593 .12642 .09341 .15195 .09875 .17613 .10242 .20136 .10503 .22458 .10651 .25191 .10731 .27462 .10734 .30195 .10678 .35017 .10471 .37685 .10320 .40344 .10157 .42607 .10012 .45228 .09836 .47432 .09680 .49983 .09488 .52478 .09280 .55306 .09013 .57414 .08788 .60250 .08445 .62408 .08153 .64961 .07770 .67575 .07339 .70240 .06864 .72617 .06416 .74966 .05956 .77674 .05412 .80302 .04870 .82446 .04422 .85023 .03874 .87504 .03337 .90244 .02737 .92463 .02238 .95022 .01657 .97593 .01034 1.00000 .00378 0.00000 0.00000 .00106 -.00728 .00248 -.01063 .00765 -.01683 .01338 -.02096 .01991 -.02441 .03183 -.02945 .04187 -.03294 .05110 -.03573 .07203 -.04101 .10088 -.04665 .12531 -.05040 .15156 -.05374 .17603 -.05633 .20151 -.05851 .22487 -.06016 .25229 -.06167 .27686 -.06259 .30180 -.06323 .32330 -.06355 .35239 -.06367 .37431 -.06353 .40000 -.06312 .42580 -.06243 .45148 -.06146 .47321 -.06042 .50145 -.05869 .52561 -.05681 .55215 -.05424 .57495 -.05155 .60089 -.04793 .62389 -.04432 .65070 -.03976 .67458 -.03552 .69911 -.03104 .72419 -.02632 .74967 -.02148 .77634 -.01652 .80123 -.01216 .82480 -.00841 .85026 -.00485 .87444 -.00195 .90007 .00032 .92418 .00147 .95022 .00160 .97586 .00013 1.00000 -.00354 |
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Polars for NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ls417mod-il | 50,000 | 9 | 24.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417mod-il | 50,000 | 5 | 26.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417mod-il | 100,000 | 9 | 33.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417mod-il | 100,000 | 5 | 41.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417mod-il | 200,000 | 9 | 52.5 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417mod-il | 200,000 | 5 | 57.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417mod-il | 500,000 | 9 | 79.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417mod-il | 500,000 | 5 | 81.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417mod-il | 1,000,000 | 9 | 103 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417mod-il | 1,000,000 | 5 | 100.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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