Add to ORKGA wind tunnel investigation has been conducted to determine the longitudinal and lateral aerodynamic characteristics of a model of a supersonic cruise fighter configuration with a design Mach number of 2.60. The configuration is characterized by a highly swept arrow wing twisted and cambered to minimize supersonic drag due to lift, twin wing mounted vertical tails, and an aft mounted integral underslung duel-engine pod. The investigation also included tests of the configuration with larger outboard vertical tails and with small nose strakes
The effects of external fuel tanks and externally mounted rocket packets on the drag characteristics...
A variable sweep fighter configuration with the wing in the 22 deg sweep position having leading edg...
A general research fighter model was tested in the Langley 7 by 10-foot high speed tunnel at a Mach ...
An investigation was made in the Langley 8-foot transonic tunnel and the Langley Unitary Plan wind t...
Two 0.085-scale full span wind-tunnel models of a Mach 1.60 design supercruiser configuration were t...
An investigation was made in the Langley Unitary Plan wind tunnel at Mach numbers of 2.30, 2.96, and...
Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft...
The aerodynamic characteristics of an advanced twin-engine fighter aircraft designed for supersonic ...
An investigation has been made in the Mach number range from 0.50 to 2.86 to determine the longitudi...
The longitudinal aerodynamic characteristics of a fighter airplane concept has been determined throu...
An investigation has been conducted at Mach numbers ranging from 0.06 to 0.94 to determine the effec...
Tests were made in the Langley 8-foot high-speed tunnel to investigate the aerodynamic characteristi...
An investigation has been conducted to determine the effects of wing camber and twist on the longitu...
The aerodynamic characteristics of a six-engine (four lift, two lift-cruise) lift-engine model obtai...
An investigation w a s made at high subsonic speeds of a model of a twin-engine swept-wing f ighter-...
The effects of external fuel tanks and externally mounted rocket packets on the drag characteristics...
A variable sweep fighter configuration with the wing in the 22 deg sweep position having leading edg...
A general research fighter model was tested in the Langley 7 by 10-foot high speed tunnel at a Mach ...
An investigation was made in the Langley 8-foot transonic tunnel and the Langley Unitary Plan wind t...
Two 0.085-scale full span wind-tunnel models of a Mach 1.60 design supercruiser configuration were t...
An investigation was made in the Langley Unitary Plan wind tunnel at Mach numbers of 2.30, 2.96, and...
Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft...
The aerodynamic characteristics of an advanced twin-engine fighter aircraft designed for supersonic ...
An investigation has been made in the Mach number range from 0.50 to 2.86 to determine the longitudi...
The longitudinal aerodynamic characteristics of a fighter airplane concept has been determined throu...
An investigation has been conducted at Mach numbers ranging from 0.06 to 0.94 to determine the effec...
Tests were made in the Langley 8-foot high-speed tunnel to investigate the aerodynamic characteristi...
An investigation has been conducted to determine the effects of wing camber and twist on the longitu...
The aerodynamic characteristics of a six-engine (four lift, two lift-cruise) lift-engine model obtai...
An investigation w a s made at high subsonic speeds of a model of a twin-engine swept-wing f ighter-...
The effects of external fuel tanks and externally mounted rocket packets on the drag characteristics...
A variable sweep fighter configuration with the wing in the 22 deg sweep position having leading edg...
A general research fighter model was tested in the Langley 7 by 10-foot high speed tunnel at a Mach ...