Transonic Simple Straked Delta Wing
Abstract
The unsteady transonic flow during manoeuvres of fighters is not very well understood. For instance, large time delays and severe dynamic overshoots in normal force may occur, which cannot be predicted accurately by numerical methods. As a consequence to be conservative structures must be over-designed or flight envelopes must be unnecessarily restricted There fore, a better understanding of the unsteady transonic flows, which occur during maneuvers, is of interest for the development and operation of fighters. This data set relates to an unsteady transonic wind tunnel test, on a highly instrumented semi-span simple straked delta wing model. Harmonic pitch as well as manoeuvre simulations were performed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 2000
- Accession Number
- ADP010728
Entities
People
- Evert G. Geurts
Organizations
- National Aerospace Laboratory