An experiment was performed on a low-aspect ratio wing to define the limits of the validity of codes which are used to predict the flow over modern fighter configurations. The focus of the experiment is to provide data at or near the true operating conditions of transonic aircraft. The Reynolds numbers reached in this experiment reproduce those experienced by an aircraft with a 5-m root chord, flying at 14 to 16 km, from Mach 0.6 to 0.8. The angle-of-attack range of the experiment extends into the regime of leading-edge separation.
Low aspect ratio wing code validation experiment
1992-01-01
Conference paper
No indication
English
Low aspect ratio wing code validation experiment
Tema Archive | 1993
|Low aspect ratio wing code validation experiment
NTRS | 1993
|Low aspect ratio wing code validation experiment
AIAA | 1992
|Low Aspect Ratio Wing Code Validation Experiment
AIAA | 1993
|Low Aspect Ratio Wing Code Validation Experiment
Online Contents | 1993
|