Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 54
Book Description
Transonic Longitudinal Aerodynamic Characteristics of a Variable-sweep Fighter Model Having Body-mounted Nacelles
Author: Transonic Longitudinal Aerodynamic Characteristics of a Variable-sweep Tactical-fighter Model with Wing Sweeps of 25, 65, 85, and 160 Degrees
Author: Static Longitudinal and Lateral Aerodynamic Characteristic at a Mach Number of 2.20 of a Variable Sweep Fighter Airplane Configuration Having Body Mounted Nacelles with Vertical Ramp Inlets
Author: Preliminary Investigation of Subsonic and Transonic Longitudinal Aerodynamic Characteristics of a Variable-sweep Airplane Configuration Having Externally Mounted Engines
Author: Transonic Longitudinal Aerodynamic Characteristics of an STOL Fighter-bomber Model with a Variable-sweep Wing
Author: Transonic Aerodynamic Characteristics of a Variable-sweep Airplane Configuration Having a 12-percent-thick Wing and an Inboard Pivot Location
Author: Ralph P. BielatPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 84
Book Description
Transonic Longitudinal Aerodynamic Characteristics of a Variable-sweep Tactical Fighter Model with Wing Sweeps of 26 Deg and 72.5 Deg
Author: Transonic Longitudinal Aerodynamic Effects of Sweeping Up the Rear of the Fuselage of a Rocket-propelled Airplane Model Having No Horizontal Tail
Author: James H. ParksPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 36
Book Description
Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches
Author: Charles F. WhitcombPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 34
Book Description
An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
Author: Richard J. Re