Browse Topic: Canards

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An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications - QA Test Tatsiana01-17-01-000104/19/2023
Abstract In subsonic aircraft design, the aerodynamic performance of aircraft is compared meaningfully at a system level by evaluating their range and endurance, but cannot do so at an aerodynamic level when using lift and drag coefficients, CL and CD , as these often result in misleading results for different wing reference areas. This Part I of the article (i) illustrates these shortcomings, (ii) introduces a dimensionless number quantifying the induced drag of aircraft, and (iii) proposes an aerodynamic equation of state for lift, drag, and induced drag and applies it to evaluate the aerodynamics of the canard aircraft, the dual rotors of the hovering Ingenuity Mars helicopter, and the composite lifting system (wing plus cylinders in Magnus effect) of a YOV-10 Bronco. Part II of this article applies this aerodynamic equation of state to the flapping flight of hovering and forward-flying insects. Part III applies the aerodynamic equation of state to some well-trodden cases in fluid
Burgers, Phillip
Journal Article
An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications - QA Test Tatsiana01-17-01-0001-TEST-REC04/19/2023
Abstract In subsonic aircraft design, the aerodynamic performance of aircraft is compared meaningfully at a system level by evaluating their range and endurance, but cannot do so at an aerodynamic level when using lift and drag coefficients, CL and CD , as these often result in misleading results for different wing reference areas. This Part I of the article (i) illustrates these shortcomings, (ii) introduces a dimensionless number quantifying the induced drag of aircraft, and (iii) proposes an aerodynamic equation of state for lift, drag, and induced drag and applies it to evaluate the aerodynamics of the canard aircraft, the dual rotors of the hovering Ingenuity Mars helicopter, and the composite lifting system (wing plus cylinders in Magnus effect) of a YOV-10 Bronco. Part II of this article applies this aerodynamic equation of state to the flapping flight of hovering and forward-flying insects. Part III applies the aerodynamic equation of state to some well-trodden cases in fluid
Burgers, Phillip
Journal Article
An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications01-17-01-000104/19/2023
In subsonic aircraft design, the aerodynamic performance of aircraft is compared meaningfullyby evaluating their range and endurance, but cannot do so atwhen using lift and drag coefficients,and, as these often result in misleading results for different wing reference areas. This Part I of the article (i) illustrates these shortcomings, (ii) introduces a dimensionless number quantifying the induced drag of aircraft, and (iii) proposes anfor lift, drag, and induced drag and applies it to evaluate the aerodynamics of the canard aircraft, the dual rotors of the hoveringMars helicopter, and the composite lifting system (wing plus cylinders in Magnus effect) of a YOV-10. Part II of this article applies this aerodynamic equation of state to the flapping flight of hovering and forward-flying insects. Part III applies the aerodynamic equation of state to some well-trodden cases in fluid mechanics found in fluid-mechanics textbooks.
Burgers, Phillip
Journal Article
Numerical Analysis of Asymmetric Canard-Wing System in Detroit Flying Cars2019-01-136103/19/2019
A numerical simulation system of airflow around the Detroit Flying Cars-Wild Dream 1 (WD-1) is introduced. It involves the application of FVM, the mesh-independence system, boundary conditions and the verification of the simulation conditions to NACA airfoil data and the discussion of technological treatments corresponding to the evaluation of asymmetric wings. The present work is investigating the aerodynamic behavior of an asymmetric canard-wing system used on the Detroit Flying Cars-WD 1 model. The work involves the application of Finite Volume Method (FVM), the mesh-independence system, boundary conditions and the verification of simulation conditions to NACA airfoil data using OpenFOAM software. The Reynolds number based on free stream velocity and root chord is 5X106. Based on the Coefficient of Lift and Coefficient of Drag obtained from the analysis, the effect of canards on the wings, the distance between the canard trailing edge and the leading edge of the wings and the
Kocherla, Isaac Shanth, Yu, ChenXing
Technical Paper
Use of ILTV Control Laws for LaNCETS Flight ResearchTBMG-872511/01/2010
A report discusses the Lift and Nozzle Change Effects on Tail Shock (LaNCETS) test to investigate the effects of lift distribution and nozzle-area ratio changes on tail shock strength of an F-15 aircraft. Specific research objectives are to obtain in-flight shock strength for multiple combinations of nozzle-area ratio and lift distribution; compare results with pre-flight prediction tools; and update predictive tools with flight results. The objectives from a stability and control perspective are to ensure adequate aircraft stability for the changes in lift distribution and plume shape, and ensure manageable transient from engaging and disengaging the ILTV research control laws. In order to change the lift distribution and plume shape of the F-15 aircraft, a decade-old Inner Loop Thrust Vectoring (ILTV) research control law was used. Flight envelope expansion was performed for the test configuration and flight conditions prior to the probing test points.
Magazine Article
Excitations for Rapidly Estimating Flight-ControlTBMG-9307/01/2006
A flight test on an F-15 airplane was performed to evaluate the utility of prescribed simultaneous independent surface excitations (PreSISE) for real-time estimation of flight-control parameters, including stability and control derivatives. The ability to extract these derivatives in nearly real time is needed to support flight demonstration of intelligent flight-control system (IFCS) concepts under development at NASA, in academia, and in industry. Traditionally, flight maneuvers have been designed and executed to obtain estimates of stability and control derivatives by use of a post-flight analysis technique. For an IFCS, it is required to be able to modify control laws in real time for an aircraft that has been damaged in flight (because of combat, weather, or a system failure).
Magazine Article
Conformably Stowable CanardTBMG-2954202/01/2001
An improved secondary wing system of the canard type has been invented to improve performance and increase efficiency of airplanes capable of flight at supersonic and high subsonic speeds. Canards, including small forward-mounted secondary wings, are used to increase the total wing surface areas of airplanes in order to improve their low-speed lift-to-drag ratios and trim characteristics. Although canards have been used on supersonic airplanes to increase low-speed performance, heretofore the designs of canards have not provided for optimal high-speed performance and aerodynamic efficiency.
Magazine Article
Wind-Tunnel Measurements of Wing-Canard Interference and a Comparison with Various Theories81057502/01/1981
CANARD-CONFIGURED AIRCRAFT DESIGNS have played a historic role in aeronautical research. However, only in the past decade or two has a canard been incorporated into a significant number of aircraft designs. Powered flight began with the Wright Flyer, which was a canard-configured aircraft. Unfortunately, however, that aircraft was longitudinally unstable and the misconception arose that all canard aircraft would be unstable in pitch, irrespective of the placement of the center of gravity. In the early years of aircraft development, the canard concept was dropped in favor of conventional tailaft designs. It was not until the 1960s that canards were again seriously considered for several high-speed, designs. For example, in the United States’ supersonic transport program, a canard was initially considered; because of several problems with aerodynamic interference, however, the idea was abandoned. For example, the canard wake passed around the vertical stabilizer and resulted in erratic
Feistel, T. W., Corsiglia, V. R., Levin, D. B.
Technical Paper
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