FAUVEL 14% AIRFOIL (fauvel-il)
FAUVEL 14% AIRFOIL - Fauvel 14% flying wing airfoil
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(fauvel-il) FAUVEL 14% AIRFOIL Fauvel 14% flying wing airfoil Max thickness 14% at 25.2% chord. Max camber 2.5% at 25.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FAUVEL 14% AIRFOIL
18. 18.
0.0000000 0.0000000
0.0011073 0.0073763
0.0139486 0.0314635
0.0265991 0.0425664
0.0518005 0.0579806
0.0769359 0.0689001
0.1020302 0.0770231
0.1521485 0.0884749
0.2021831 0.0942337
0.2521488 0.0952981
0.3020616 0.0927669
0.4017920 0.0812125
0.5014448 0.0643644
0.6010416 0.0437210
0.7007105 0.0279716
0.8004306 0.0157180
0.9002036 0.0070599
1.0000000 -.0000000
0.0000000 0.0000000
0.0009064 -.0063070
0.0131976 -.0196743
0.0256179 -.0242523
0.0505054 -.0302122
0.0754237 -.0340747
0.1003567 -.0369383
0.1502402 -.0414671
0.2001560 -.0437985
0.2500953 -.0445319
0.3000346 -.0452652
0.3999131 -.0467320
0.4997917 -.0481987
0.5997362 -.0451710
0.6997366 -.0383478
0.7997838 -.0283285
0.8998751 -.0153129
1.0000000 -.0000000
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Polars for FAUVEL 14% AIRFOIL (fauvel-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fauvel-il | 50,000 | 9 | 9.9 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 50,000 | 5 | 18.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 100,000 | 9 | 22.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 100,000 | 5 | 39.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 200,000 | 9 | 57.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 200,000 | 5 | 60.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 500,000 | 9 | 89.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 500,000 | 5 | 82.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fauvel-il | 1,000,000 | 9 | 106.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fauvel-il | 1,000,000 | 5 | 96 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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