| 摘要 |
The present invention provides improvements for supersonic aircraft, joined-wing aircraft and sonic boom reduction, separately and in combination, for long range supersonic cruise aircraft with reduced sonic boom loudness. Several designs for integrating and supporting a propulsion system with reduced transonic and supersonic drag are disclosed. A tail-braced wing configuration for supporting a propulsion system installation with minimum draft interference and reduced structural weight is provided. A method for designing an improved wing in the presence of a propulsion system supersonic pressure disturbance is also provided. The drag reducing features synergistically help in meeting a shaped sonic boom minimized lift and area distribution. The tail-braced wing design and other asymmetric area distribution features further reduce the shaped sonic boom minimum. For example, boom pressure at audible frequencies may be reduced 30 to 100 times for business jets. |
