Wind tunnel measurements of an ogive delta wing model with 64.4 deg leading edge sweepback were carried out in a supersonic transonic l sq meter wind tunnel. Static and dynamic tests were carried out over a range of mach numbers from low transonic speed up to M l.92, 3- 5-, and 6-component strain gauge balance measurements and flow visualization tests were also performed. The angle of attack range includes angles at which vortex breakdown occurs.
Measurements of Static Stability Coefficients of an Ogive delta Wing Model at Transonic and Supersonic Speeds
1974
112 pages
Report
Keine Angabe
Englisch
The oblique wing—aircraft design for transonic and low supersonic speeds
Elsevier | 1976
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