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 Degree Sweepback
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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 Degree Sweepback
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Author : Charles T. D'Aiutolo
language : en
Publisher:
Release Date : 1955
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 Degree Sweepback written by Charles T. D'Aiutolo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with categories.
Free Flight Experience Of The Lateral Stability Characteristics At Low Lift Of A 45 Degree Swept Wing Rocket Propelled Model Equipped With A Nonlinear Yaw Rate Damper System At Mach Numbers From 0 76 To 1 73
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Author : Charles T. D'Aiutolo
language : en
Publisher:
Release Date : 1957
Free Flight Experience Of The Lateral Stability Characteristics At Low Lift Of A 45 Degree Swept Wing Rocket Propelled Model Equipped With A Nonlinear Yaw Rate Damper System At Mach Numbers From 0 76 To 1 73 written by Charles T. D'Aiutolo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
A low-lift lateral stability investigation was conducted with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system in the Mach number range from 0.76 to 1.73. The lateral oscillations due to periodic yawing disturbances were analyzed to determine the lateral characteristics of the airframe-yaw-rate-damper combination. In addition, due to a dead spot in the operation of the yaw-rate damper system, it was possible to determine the lateral derivatives of the model when the Mach number was greater than 1.2 by the use of the time-vector method while the damper was essentially inoperative. The data were further interpreted in terms of full-scale-airplane flying qualities.
Supersonic Aerodynamic Characteristics Of A Low Drag Aircraft Configuration Having An Arrow Wing Of Aspect Ratio 1 86 And A Body Of Fineness Ratio 20
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Author : Warren Gillespie (Jr)
language : en
Publisher:
Release Date : 1960
Supersonic Aerodynamic Characteristics Of A Low Drag Aircraft Configuration Having An Arrow Wing Of Aspect Ratio 1 86 And A Body Of Fineness Ratio 20 written by Warren Gillespie (Jr) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with categories.
A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
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
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Author : Charles T. D'Aiutolo
language : en
Publisher:
Release Date : 1956
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 written by Charles T. D'Aiutolo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Airplanes categories.
A rocket-propelled model of an airplane configuration having thin, highly tapered, 45 degree sweptback surfaces was tested in the Mach number range of 0.80 to 1.57 to obtain the lateral stability characteristics of the configuration.
Static Lateral Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configuration
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Author : Kenneth W. Goodson
language : en
Publisher:
Release Date : 1961
Static Lateral Characteristics At High Subsonic Speeds Of A Complete Airplane Model With A Highly Tapered Wing Having The 0 80 Chord Line Unswept And With Several Tail Configuration written by Kenneth W. Goodson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Stability of airplanes, Lateral categories.
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The aspect-ratio-3.50 wing had a taper of 0.067 and an unswept 0.80 chord line. The complete model was tested with a wing-chord-plane tail, a T-tail, and a biplane tail (combined T-tail and wing-chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 over a range of angle of attack of about ±20° and a range of sideslip of -15° to 13°. Some data were obtained with the horizontal stabilizer deflected. A few tests were also made with the wing tips clipped to an aspect ratio of 3.00.
Lateral Stability Investigation At Mach Numbers From 0 8 To 1 7 Of Two Rocket Boosted Models Of An Airplane Configuration With A 45 Degree Swept Wing And A Low Horizontal Tail
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Author : John C. McFall
language : en
Publisher:
Release Date : 1957
Lateral Stability Investigation At Mach Numbers From 0 8 To 1 7 Of Two Rocket Boosted Models Of An Airplane Configuration With A 45 Degree Swept Wing And A Low Horizontal Tail written by John C. McFall and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
Rocket-boosted free-flight tests of two models of an airplane configuration having a 45 degree swept wing and a low horizontal-tail position have provided lateral stability derivatives and control effectiveness data for a Mach number range from 0.8 to 1.7. The experimental lateral stability derivatives presented are corrected to rigid conditions and compared with theoretically calculated rigid derivatives. The results are presented without detailed analysis.
Some Effects Of Aircraft Configuration On Static Longitudinal And Directional Stability Characteristics At Supersonic Mach Numbers Below 3
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Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1959
Some Effects Of Aircraft Configuration On Static Longitudinal And Directional Stability Characteristics At Supersonic Mach Numbers Below 3 written by M. Leroy Spearman and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Aerodynamics, Supersonic categories.
Free Flight Experience Of The Lateral Stability Characteristics At Low Lift Of A 45 Swept Wing Rocket Propelled Model Equipped With A Nonlinear Yaw Rate Damper System At Mach Numbers From 0 76 To 1 73
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Author : Charles T. D'Aiutolo
language : en
Publisher:
Release Date : 1957
Free Flight Experience Of The Lateral Stability Characteristics At Low Lift Of A 45 Swept Wing Rocket Propelled Model Equipped With A Nonlinear Yaw Rate Damper System At Mach Numbers From 0 76 To 1 73 written by Charles T. D'Aiutolo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Airplanes categories.
Longitudinal Stability And Drag Characteristics At Mach Numbers From 0 75 To 1 5 Of An Airplane Configuration Having A 60 Degrees Swept Wing Of Aspect Ratio 2 24 As Obtained From Rocket Propelled Model
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Author : A. James Vitale
language : en
Publisher:
Release Date : 1952
Longitudinal Stability And Drag Characteristics At Mach Numbers From 0 75 To 1 5 Of An Airplane Configuration Having A 60 Degrees Swept Wing Of Aspect Ratio 2 24 As Obtained From Rocket Propelled Model written by A. James Vitale and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with categories.
Static Stability Characteristics Of A Series Of Hypersonic Boost Glide Configurations At Mach Numbers Of 1 41 And 2 01
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Author : Gerald V. Foster
language : en
Publisher:
Release Date : 1959
Static Stability Characteristics Of A Series Of Hypersonic Boost Glide Configurations At Mach Numbers Of 1 41 And 2 01 written by Gerald V. Foster and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with Gliders (Aeronautics) categories.