Study of the canard configuration with particular reference to transonic flight characteristics and low-speed characteristics at high lift
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Mathews, Charles W↗
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Low-speed static longitudinal stability characteristics of a canard model having a 60 degrees triangular wing and horizontal tail
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Bates, William R↗
Low-speed static lateral stability characteristics of a canard model having a 60 degrees triangular wing and horizontal tail
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Bates, William R↗
Determination by the Free-fall Method of the Drag and Longitudinal Stability and Control Characteristics of a Canard Model at Transonic Speeds
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Kraft, Christopher C , Jr↗
A theoretical investigation of the influence of auxiliary damping in pitch on the dynamic characteristics of a proportionally controlled supersonic canard missile configuration
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Nelson, Walter C↗
Wing-flow Measurements of Longitudinal Stability and Control Characteristics of a Canard Airplane Configuration with a 45 Degree Sweptback Wing and a Triangular All-movable Control Surface
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Crane, Harold L↗
Low-speed Static Stability Characteristics of a Canard Model with a 45 Degree Sweptback Wing and a 60 Degree Triangular Horizontal Control Surface
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Draper, John W↗
Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section
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Johnson, Joseph L↗
Wind-tunnel Investigation at Mach Numbers of 1.5 and 2.0 of a Canard Missile Configuration
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Spahr, J Richard↗
Theoretical Investigation of an Automatic Control System with Primary Sensitivity to Normal Accelerations as Used to Control a Supersonic Canard Missile Configuration
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Seaberg, Ernest C↗
A Theoretical Investigation of the Influence of Autopilot Natural Frequency upon the Dynamic Performance Characteristics of a Supersonic Canard Missile Configuration with a Pitch-attitude Control System
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Passera, Anthony L↗
The Static Longitudinal Characteristics at Mach Numbers up to 0.95 of a Triangular-wing Canard Model Having a Triangular Control
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Stephenson, Jack D↗
Influence of a Canard-type Control Surface on Flow Field in Vicinity of Symmetrical Fuselage at Mach Numbers 1.8 and 2.0
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Wise, George A↗
Longitudinal stability and control characteristics of a canard missile configuration for Mach numbers from 1.1 to 1.93 as determined from free-flight and wind-tunnel investigation
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Curfman, Howard J , Jr↗
Performance Characteristics of a Normal-shock Side Inlet Located Downstream of a Canard Control Surface at Mach Numbers of 1.5 and 1.8/
The performance characteristics of a downward canted normal-shock side (scoop) inlet located downstream of a triangular control surface are presented for free-stream Mach numbers of 1.5 and 1.8 in terms of total pressure recovery and mass flow ratio for various boundary-layer removal systems,angles of attack, control surface deflections and adverse yaw. An engine operating condition for a hypothetical turbojet engine is established, and the match point characteristics of the engine-inlet configuration are summarized. 520::It is shown that the diffuser performance increases with increased boundary-layer removal and decreases because of the presence of the wake from the forward control surface. At the higher angles of attack the wake passes over the inlet and does not affect the inlet performance. Adverse yaw reduces the total pressure recovery values below those for the unawed case. Magnitudes of the total pressure recovery were below the theoretical normal-shock recovery for the respective test Mach numbers.
INLETS, SIDE - DUCTED BODIES↗
Influence of a canard-type control surface on the internal and external performance characteristics of nacelle-mounted supersonic diffusers (conical centerbody) at a rearward body station for a Mach number of 2.0
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Obery, L J↗
Influence of Fuselage and Canard-type Control Surface on the Flow Field Adjacent to a Rearward Fuselage Station at a Mach Number of 2.0 : Data Presentation
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Obery, Leonard J↗
A Theoretical Investigation of the Effect of a Target Seeker Sensitive to Pitch Attitude on the Dynamic Stability and Response Characteristics of a Supersonic Canard Missile Configuration
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Gates, Ordway B , Jr↗