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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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.
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.
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.
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.
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.
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.
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.
Stability And Control Characteristics At Mach Numbers Of 2 50 3 00 And 3 71 Of A Variable Wing Sweep Configuration With Outboard Wing Panels Swept Back 75
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Author : Gerald V. Foster
language : en
Publisher:
Release Date : 1960
Stability And Control Characteristics At Mach Numbers Of 2 50 3 00 And 3 71 Of A Variable Wing Sweep Configuration With Outboard Wing Panels Swept Back 75 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 1960 with Aerodynamics, Supersonic categories.
Static Stability And Separation Characteristics Of A Two Stage Rocket Configuration At Mach Numbers From 1 57 To 4 50
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Author : Kenneth L. Turner
language : en
Publisher:
Release Date : 1960
Static Stability And Separation Characteristics Of A Two Stage Rocket Configuration At Mach Numbers From 1 57 To 4 50 written by Kenneth L. Turner and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aerodynamics, Supersonic categories.
Longitudinal Stability And Control Characteristics Of A Two Place All Weather Fighter Airplane Between Mach Numbers Of 0 80 And 2 00 Obtained From The Flight Test Of A Rocket Boosted Model
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Author :
language : en
Publisher:
Release Date : 1959
Longitudinal Stability And Control Characteristics Of A Two Place All Weather Fighter Airplane Between Mach Numbers Of 0 80 And 2 00 Obtained From The Flight Test Of A Rocket Boosted Model written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1959 with categories.