|
US2005224640A1
|
|
Methods for incorporating area ruled surfaces in a supersonic aircraft
|
|
EP1694560A2
|
|
Area ruling for supersonic vehicles
|
|
US2006058985A1
|
|
Adjoint-based design variable adaptation
|
|
WO2005044661A2
|
|
Supersonic aircraft with aerodynamic control
|
|
WO2005062743A2
|
|
Supersonic aircraft with aerodynamic tail structure
|
|
WO2005050601A2
|
|
Display systems for a device
|
|
US2005116107A1
|
|
Area ruling for vertical stabilizers
|
|
US2005121555A1
|
|
Mach weighted area ruling for supersonic vehicles
|
|
US2005116116A1
|
|
Wing employing leading edge flaps and winglets to achieve improved aerodynamic performance
|
|
US6854687B1
|
|
Nacelle integration with reflexed wing for sonic boom reduction
|
|
US6824092B1
|
|
Aircraft tail configuration for sonic boom reduction
|
|
US2005103929A1
|
|
Supersonic aircraft with channel relief control
|
|
US2005067526A1
|
|
Wing gull integration nacelle clearance, compact landing gear stowage, and sonic boom reduction
|
|
US2005051666A1
|
|
Aircraft with active center of gravity control
|
|
US2005045763A1
|
|
Aircraft lift device for low sonic boom
|
|
US2005045764A1
|
|
Canard position and dihedral for boom reduction and pitch/directional control
|
|
US2005067525A1
|
|
Aircraft thickness/camber control device for low sonic boom
|
|
US2005098681A1
|
|
System and method for controlling the acoustic signature of a device
|
|
US2005007261A1
|
|
Display system for operating a device with reduced out-the-window visibility
|
|
US2005178900A1
|
|
Forward inboard retracting main landing gear
|
