Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Effects of Wing Height on the Stability and Control Characteristics at a Mach Number of 2.01 of a Canard Airplane Configuration with a 70 Deg Delta Wing
Author: Effects of Deflected Wing Tips on the Aerodynamic Characteristics of a Canard Configuration at Mach Numbers from 0.7 to 3.5
Author: Victor L. PetersonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 180
Book Description
Effects of Wing Position and Vertical-tail Configuration on Stability and Control Characteristics of a Jet-powered Delta-wing Vertically Rising Airplane Model
Author: Powell M. LovellPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 42
Book Description
An investigation has been conducted to determine the effects of wing position and vertical tail configuration on the stability and control characteristics of a jet-powered delta-wing vertically rising airplane model. A ducted-fan powerplant was used because there was no hot-jet powerplant of sufficiently small size and adequate reliability available. In addition to conventional flap-type control surfaces on the wings and vertical tails, the model had jet-reaction controls provided by movable eyelids at the rear of the tail pipe and by air bled from the main duct and exhausted through movable nozzles near the wing tips. The investigation consisted of flight and force tests of three model configurations: a high wing with a top-mounted vertical tail, a high wing with top- and bottom-mounted vertical tails, and a low wing with the top-mounted vertical tail. The flight tests, which were made in the Langley full-scale tunnel, represented slow constant-altitude transitions from hovering to normal unstalled forward flight.
Aerodynamic Characteristics at Mach 6 of a Hypersonic Research Airplane Concept Having a 70 ̊swept Delta Wing
Author: Louis E. ClarkPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 68
Book Description
Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86
Author: Samuel M. DollyhighPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 126
Book Description
An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.
Stability and Control Characteristics at Mach Numbers of 2.50, 3.00, and 3.71 of a Variable- Wing-sweep Configuration with Outboard Wing Panels Swept Back 75°
Author: Gerald V. FosterPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38
Book Description
Effects of Wing Incidence on the Longitudinal Trim Characteristics of a Cambered 70° Delta-wing Configuration at Mach Numbers 3.0 to 5.0
Author: Warren F. AhtyePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
Book Description
Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.01 of a Tailless Delta V/STOL Configuration Having Variable-sweep Wing Panels
Author: M. Leroy SpearmanPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Book Description
Aerodynamic Characteristics at Transonic and Supersonic Speeds of a Rocket-propelled Airplane Configuration Having a Diamond-plan-form Wing Aspect Ration 3.08 and a Low, Swept Horizontal Tail
Author: Alan B. KehletPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 42
Book Description
Aerodynamic Characteristics of a Tailless Fixed-wing Supersonic Transport Configuration at Mach Number 2.20
Author: Gerald V. FosterPublisher:
ISBN:
Category : Airplanes, Tailless
Languages : en
Pages : 54
Book Description
