This paper focuses on Reynolds number scaling (RNS) at transonic speeds for military aircraft development. RNS has been used in the development of aircraft for decades because most development wind tunnels have not had the capability of providing full scale flight Reynolds number. This paper discusses the importance of RNS and why it must be used for the foreseeable future. Two empirical methods and one computational fluid dynamics (CFD) method are shown to illustrate some of the issues and deficiencies involved with RNS. Wind tunnel effects on aerodynamic data that produce pseudo Reynolds number effects and that must be taken into account are also discussed. Finally, it is argued that improvements in RNS and proper accounting for wind tunnel effects on aerodynamic data can significantly contribute to the reduction in the time and cost of aircraft development.
Reynold Number Scaling at Transonic Speeds
1998
19 pages
Report
Keine Angabe
Englisch
Reynolds number scaling at transonic speeds
AIAA | 1998
|Cavity drag at transonic speeds
Online Contents | 1993
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