USA 98 AIRFOIL (usa98-il)
USA 98 AIRFOIL - USA-98 airfoil
| Details | Dat file | Parser | |
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(usa98-il) USA 98 AIRFOIL USA-98 airfoil Max thickness 14.3% at 30% chord. Max camber 6.4% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 98 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0250000 0.0410000
0.0500000 0.0580000
0.1000000 0.0830000
0.2000000 0.1120000
0.3000000 0.1260000
0.4000000 0.1290000
0.5000000 0.1230000
0.6000000 0.1100000
0.7000000 0.0910000
0.8000000 0.0690000
0.9000000 0.0450000
1.0000000 0.0090000
0.0000000 0.0000000
0.0250000 -.0340000
0.0500000 -.0375000
0.1000000 -.0360000
0.2000000 -.0295000
0.3000000 -.0170000
0.4000000 -.0030000
0.5000000 0.0090000
0.6000000 0.0160000
0.7000000 0.0190000
0.8000000 0.0170000
0.9000000 0.0090000
1.0000000 0.0000000
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Polars for USA 98 AIRFOIL (usa98-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa98-il | 50,000 | 9 | 8.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 5 | 26.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 9 | 54.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 5 | 59.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 9 | 84.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 5 | 84.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 9 | 120.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 5 | 112.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 9 | 147.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 5 | 124.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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