SST PHASE IIA.
Abstract
The effect of an L/D increase from 7.65 to 7.95 was an improvement in range of 215 n.mi., at a maximum climb sonic boom overpressure limit of 2.0 psf and 110 n.mi. at delta P = 2.5. Wind tunnel tests showed that more powerful control forces can be developed by an increase in tail size, reduction in tail aspect ratio, and addition of a slot to the elevator. Studies to determine the best approach for both longitudinal stability and flight control were continuing. Recent testing showed that automatic restart without bypass door or centerbody movement can be provided with secondary bypass doors located forward of the inlet throat. Using these forward doors, the inlet will restart at all supersonic Mach numbers. Model tests showed that the aerodynamic 'bellmouth,' formed by engine bleed air ejected at the cowl lip for de-icing, will increase inlet recovery by approximately 3% at static conditions. A significant milestone was passed; testing of the full scale wing pivot began. Six hundred cycles were successfully completed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1964
- Accession Number
- AD0479158
Entities
Organizations
- Boeing