NASA STI Repository (National Aeronautics and Space Administration) · 1977 · 19 citations · 3 references
Open access
EngineeringAerospace EngineeringMechanical EngineeringAerodynamicsAircraft DesignFlight MechanicsAerodynamic DesignAirfoil TheoryLiftWing AerodynamicsWing DesignWing TheoryAircraft Aerodynamic DesignCanard ConfigurationDragInduced DragLift-to-drag RatioStabilizer EfficiencyStatic MarginStatic Margin Analysis
Classical drag equations were used to calculate total and induced drag and ratios of stabilizer lift to wing lift for a variety of conventional and canard configurations. The Flight efficiencies of such configurations that are trimmed in pitch and have various values of static margin are evaluated. Classical calculation methods are compared with more modern lifting surface theory.
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