An experimental wind-tunnel investigation has been carried out to determine the static longitudinal, lateral, and directional stability and control characteristics of a model of a large-body, delta-wing hypersonic research airplane concept at low speed. This investigation was conducted at a dynamic pressure of 239.4 Pa (5 psf) and a Reynolds number, based on fuselage length, of 2 million. The configuration variables included vertical fins, engine modules, canards, and a canopy. The aerodynamic results of a computer study at Mach numbers of 3 to 12 are presented. (Author)
Experimental Low-Speed and Calculated High-Speed Aerodynamic Characteristics of a Hypersonic Research Airplane Concept Having a 65 Deg Swept delta Wing
1974
73 pages
Report
No indication
English