USA 33 AIRFOIL (usa33-il)
USA 33 AIRFOIL - USA-33 airfoil
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(usa33-il) USA 33 AIRFOIL USA-33 airfoil Max thickness 14.2% at 29.9% chord. Max camber 4.9% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 33 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0120700 0.0361400
0.0243800 0.0512900
0.0491900 0.0675900
0.0740200 0.0813900
0.0988900 0.0921900
0.1487300 0.1057800
0.1986300 0.1143800
0.2985700 0.1195800
0.3986100 0.1157800
0.4987600 0.1029900
0.5989700 0.0861900
0.6992000 0.0663900
0.7994600 0.0445900
0.8997100 0.0238000
0.9498300 0.0124000
1.0000000 0.0000000
0.0000000 0.0000000
0.0127900 -.0238500
0.0253700 -.0307000
0.0504100 -.0344000
0.0754300 -.0360900
0.1004300 -.0357900
0.1503700 -.0312000
0.2003100 -.0256000
0.3002700 -.0224000
0.4002900 -.0242000
0.5003200 -.0270000
0.6003500 -.0288000
0.7003300 -.0276000
0.8002600 -.0214000
0.9001500 -.0122000
0.9500800 -.0066000
1.0000000 0.0000000
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Polars for USA 33 AIRFOIL (usa33-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa33-il | 50,000 | 9 | 7.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 100,000 | 9 | 45.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 100,000 | 5 | 47.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 200,000 | 9 | 66.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 200,000 | 5 | 60.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 500,000 | 9 | 85.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 500,000 | 5 | 67.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 1,000,000 | 9 | 93.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 1,000,000 | 5 | 67.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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