Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Book Description
Transonic Aerodynamic Characteristics of Three V/STOL Fighter Models with Variable Sweep Or Skewed Wings and Different Engine Installations
Author: Transonic Longitudinal Aerodynamic Characteristics of a Variable-sweep Fighter Model Having Body-mounted Nacelles
Author: A Summary of Research on Variable-sweep Fighter Airplanes
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
Proceedings of NASA Conference on Supersonic-Transport Feasibility Studies and Supporting Research, September 17-19, 1963, Langley Research Center, Langley Station, Hampton, Va
Author: Publisher:
ISBN:
Category : Supersonic transport planes
Languages : en
Pages : 528
Book Description
Transonic Longitudinal Aerodynamic Characteristics of an STOL Fighter-bomber Model with a Variable-sweep Wing
Author: Scientific and Technical Aerospace Reports
Author: Performance, Stability, and Control Characteristics at Transonic Speeds of Three V/STOL Airplane Configurations with Wings of Variable Sweep
Author: Arvo A. LuomaPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 206
Book Description
Transonic Aerodynamic Characteristics at a Wing Sweep of 104 Deg of a Variable-sweep Airplane Configuration with an Over and Under Engine Installation
Author: 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.