RUTAN CANARD AIRFOIL (amsoil1-il)
RUTAN CANARD AIRFOIL - Rutan AMSOIL racer canard airfoil
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(amsoil1-il) RUTAN CANARD AIRFOIL Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord. Max camber 2.1% at 42% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RUTAN CANARD AIRFOIL 38. 38. 0.00000 0.00000 .00194 .00977 .00388 .01353 .00775 .01857 .03000 .03318 .06000 .04349 .09000 .05054 .12000 .05609 .15000 .06070 .18000 .06465 .21000 .06810 .24000 .07109 .27000 .07357 .30000 .07562 .33000 .07717 .36000 .07822 .39000 .07880 .42000 .07884 .45000 .07833 .48000 .07733 .51000 .07574 .54000 .07364 .57000 .07101 .60000 .06787 .63000 .06426 .66000 .06023 .69000 .05578 .72000 .05097 .75000 .04585 .78000 .04054 .81000 .03504 .84000 .02942 .87000 .02384 .90000 .01837 .93000 .01310 .96000 .00814 .99000 .00360 1.00000 .00221 0.00000 0.00000 .00194 -.00934 .00388 -.01267 .00775 -.01690 .03000 -.02698 .06000 -.03167 .09000 -.03364 .12000 -.03465 .15000 -.03523 .18000 -.03566 .21000 -.03605 .24000 -.03640 .27000 -.03674 .30000 -.03705 .33000 -.03729 .36000 -.03740 .39000 -.03744 .42000 -.03725 .45000 -.03690 .48000 -.03632 .51000 -.03550 .54000 -.03446 .57000 -.03314 .60000 -.03159 .63000 -.02977 .66000 -.02775 .69000 -.02550 .72000 -.02310 .75000 -.02054 .78000 -.01791 .81000 -.01523 .84000 -.01260 .87000 -.01004 .90000 -.00767 .93000 -.00558 .96000 -.00380 .99000 -.00252 1.00000 -.00221 |
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Polars for RUTAN CANARD AIRFOIL (amsoil1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| amsoil1-il | 50,000 | 9 | 33 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 50,000 | 5 | 31.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 9 | 48.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 5 | 46.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 9 | 67.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 5 | 59.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 9 | 86.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 5 | 68.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 9 | 93 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 5 | 81.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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