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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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.
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.
Static Lateral Stability And Control Characteristics Of A Model Of A 45 Degree Swept Wing Fighter Airplane With Various Vertical Tails At Mach Numbers Of 1 41 1 61 And 2 01
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Author : M. Leroy Spearman
language : en
Publisher:
Release Date : 1956
Static Lateral Stability And Control Characteristics Of A Model Of A 45 Degree Swept Wing Fighter Airplane With Various Vertical Tails At Mach Numbers Of 1 41 1 61 And 2 01 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 1956 with categories.
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.
Rocket Model Investigation Of Lateral Stability Characteristics And Power Effects Of A Jet Engine Airplane Configuration With Tail Boom At Mach Numbers From 1 15 To 1 37
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Author : T. Bradley Curry
language : en
Publisher:
Release Date : 1961
Rocket Model Investigation Of Lateral Stability Characteristics And Power Effects Of A Jet Engine Airplane Configuration With Tail Boom At Mach Numbers From 1 15 To 1 37 written by T. Bradley Curry and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Aerodynamics categories.
Rocket Model Investigation Of Lateral Stability Characteristics And Power Effects Of A Jet Engine Airplane Configuration With Tail Boom At Mach Numbers From 1 15 To 1 37
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Author : T. Bradley Curry (Jr)
language : en
Publisher:
Release Date : 1961
Rocket Model Investigation Of Lateral Stability Characteristics And Power Effects Of A Jet Engine Airplane Configuration With Tail Boom At Mach Numbers From 1 15 To 1 37 written by T. Bradley Curry (Jr) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with categories.
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 Longitudinal Stability Of A Rocket Vehicle Having A Rear Facing Step Ahead Of The Stabilizing Fins
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Author : Robert J. Keynton
language : en
Publisher:
Release Date : 1961
Static Longitudinal Stability Of A Rocket Vehicle Having A Rear Facing Step Ahead Of The Stabilizing Fins written by Robert J. Keynton and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Rockets (Aeronautics) categories.
"Tests were conducted at Mach numbers of 3.96 and 4.65 in the Langley Unitary Plan wind tunnel to determine the static longitudinal stability characteristics of a fin-stabilized rocket-vehicle configuration which had a rearward facing step located upstream of the fins. Two fin sizes and planforms, a delta and a clipped delta, were tested. The angle of attack was varied from 6° to -6° and the Reynolds number based on model length was about 10 x 106. The configuration with the larger fins (clipped delta) had a center of pressure slightly rearward of and an initial normal-force-curve slope slightly higher than that of the configuration with the smaller fins (delta) as would be expected. Calculations of the stability parameters gave a slightly lower initial slope of the normal-force curve than measured data, probably because of boundary-layer separation ahead of the step. The calculated center of pressure agreed well with the measured data. Measured and calculated increments in the initial slope of the normal-force curve and in the center of pressure, due to changing fins, were in excellent agreement indicating that separated flow downstream of the step did not influence flow over the fins. This result was consistent with data from schlieren photographs."--P. 1.
Rocket Powered Model Investigation Of The Hinge Moment And Normal Force Characteristics Of A Half Diamond Tip Control On A 60 Degree Sweptback Diamond Wind Between Mach Numbers Of 0 5 And 1 3
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Author : James D. Church
language : en
Publisher:
Release Date : 1954
Rocket Powered Model Investigation Of The Hinge Moment And Normal Force Characteristics Of A Half Diamond Tip Control On A 60 Degree Sweptback Diamond Wind Between Mach Numbers Of 0 5 And 1 3 written by James D. Church and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with Airplanes categories.
A free-flight investigation has been conducted to determine normal-force and hinge-moment characteristics of a half-diamond tip control on a diamond wing having 60 degree sweptback leading edges and 30 degree sweptforward trailing edges through a range of Mach number of 0.5 to 1.3. Results indicate that the control could be so hinged that very small hinge-moments due to control deflection would be obtained at low angles of attack over the speed range tested, although nonlinear variations of hinge moment with angle of attack were present in the transonic range.
Static Stability Characteristics At Mach Numbers From 1 90 To 4 63 Of A 76 Degrees Swept Arrow Wing Model With Variations In Horizontal Tail Height Wing Height And Dihedral
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Author : Dennis E. Fuller
language : en
Publisher:
Release Date : 1967
Static Stability Characteristics At Mach Numbers From 1 90 To 4 63 Of A 76 Degrees Swept Arrow Wing Model With Variations In Horizontal Tail Height Wing Height And Dihedral written by Dennis E. Fuller and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1967 with categories.