12 research outputs found
Low-amplitude Damping-in-pitch Characteristics of Four Tailless Swept Wing-body Combinations at Mach Numbers from 0.85 to 1.30 as Obtained with Rocket-powered Models
Preliminary results of the flight investigation between Mach numbers of 0.80 and 1.36 of a rocket-powered model of a supersonic airplane configuration having a tapered wing with circular-arc sections and 40 degree sweepback
Lateral Stability Characteristics at Low Lift Between Mach Numbers of 0.85 and 1.15 of a Rocket-propelled Model of a Supersonic Airplane Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degrees Sweepback
Lateral Stability Characteristics Between Mach Numbers of 0.80 and 1.57 and Simulation of Coupled Motion at Mach Number of 1.30 of a Rocket-propelled Model of an Airplane Configuration Having Thin Highly Tapered 45 Degree Sweptback Surfaces
Preliminary Investigation of the Low-amplitude Damping in Pitch of Tailless Delta- and Swept-wing Configurations at Mach Numbers from 0.7 to 1.35
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NACA Research Memorandums
Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided
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NACA Research Memorandums
Report presenting an investigation to determine the damping-in-pitch characteristics of four rocket-powered wing-body combinations for a range of Mach numbers from 0.85 to 1.30. The models were tested at the same center-of-gravity location and had identical bodies. Information about the trim, lift, static longitudinal stability, dynamic longitudinal stability, and drag is provided
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NACA Research Memorandums
Report presenting a flight investigation using four rocket-propelled models of low-aspect-ratio tailless configurations between Mach numbers 0.7 and 1.35. The configurations investigated were a 45 degree delta model with NACA 63A010 airfoil sections parallel to free stream, a 45 degree delta-wing model with NACA 63A006 airfoil sections parallel to free stream, a 37.5 degree swept-tapered wing model with NACA 64(sub 1)A012 sections perpendicular to quarter chord, and a 39 degree swept-tapered-wing model with NACA 64A006 airfoil sections perpendicular to quarter chord. Results regarding time histories, static longitudinal stability, dynamic longitudinal stability, order of oscillation frequency, rotational damping in pitch, and drag are provided
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NACA Research Memorandums
Report presenting testing of a model of a supersonic airplane configuration with a 40 degree sweptback wing with circular-arc sections at Mach numbers 0.85 and 1.15 to obtain lateral stability data at low lift and to evaluate the test and analysis technique. Results regarding time history, trim characteristics, amplitude ratio and phase of rolling angular acceleration to angle of sideslip, sideslip derivatives, moment derivatives due to yawing, and a comparison of present data with previously obtained data are provided
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NACA Research Memorandums
Report presenting testing of a model of an airplane configuration with thin, highly tapered, 45 degree sweptback surfaces at a range of Mach numbers to obtain the lateral stability characteristics of the configuration. Results regarding the time history, trim characteristics, lateral-force derivative, vector plots, and downwash and sidewash are provided. At Mach number 1.3, the model experienced a violent combined lateral-longitudinal motion and large angles of sideslip and attack with large rolling velocities