Subsonic/Transonic Configuration Aerodynamics.
Abstract
An important region of the flight envelope of military aircraft is the transonic regime where fighter aircraft must undergo agile maneuvers, and airlift aircraft must cruise efficiently. Unfortunately it is a speed regime where wind tunnel testing is difficult, and numerical computations are not yet fully viable. Most troublesome is that exact configuration optimization criteria are lacking. Unavoidably the optimization procedure has been an ad hoc procedure, depending on the intuitive skills of the aerodynamicist. During the past decade, there has been significant progress in the development of transonic wind tunnel test techniques and computational methods. Employing these techniques, the aerodynamicist has developed many imaginative design concepts that have added to the optimization data base. It was the purpose of the symposium to review and assess these developments and project the future. Twenty nine papers comprised the meeting with three invited review papers. There was a relatively even mixture of theoretical and experimental papers with many providing test/theory comparisons. Subject matter ranged from simple wing-fuselage interference for both fighter and airlift configurations to those envolving additional components such as nacelle and pylons, powered jets, winglets, and most importantly stores and weapons.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1980
- Accession Number
- ADA094086
Entities
Organizations
- AGARD