Rocket Powered Model Investigation Of Lift Drag And Stability Of A Body Tail Configuration At Mach Numbers From 0 8 To 2 3 And Angles Of Attack Between Plus Or Minus 6 5 Degrees
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Rocket Powered Model Investigation Of Lift Drag And Stability Of A Body Tail Configuration At Mach Numbers From 0 8 To 2 3 And Angles Of Attack Between Plus Or Minus 6 5 Degrees
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Author : Warren Jr Gillespie
language : en
Publisher:
Release Date : 1954
Rocket Powered Model Investigation Of Lift Drag And Stability Of A Body Tail Configuration At Mach Numbers From 0 8 To 2 3 And Angles Of Attack Between Plus Or Minus 6 5 Degrees written by Warren Jr Gillespie and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1954 with categories.
Flying Magazine
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Author :
language : en
Publisher:
Release Date : 2002-08
Flying Magazine written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002-08 with categories.
Flying Magazine
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Author :
language : en
Publisher:
Release Date : 2002-08
Flying Magazine written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002-08 with categories.
Flying Magazine
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Author :
language : en
Publisher:
Release Date : 1966-11
Flying Magazine written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966-11 with categories.
Lift Drag And Longitudinal Stability At Mach Numbers From 1 4 To 2 3 Of A Rocket Powered Model Having A 52 5 Degree Sweptback Wing Of Aspect Ratio 3 And Inline Tail Surfaces
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Author : Warren Jr Gillespie
language : en
Publisher:
Release Date : 1955
Lift Drag And Longitudinal Stability At Mach Numbers From 1 4 To 2 3 Of A Rocket Powered Model Having A 52 5 Degree Sweptback Wing Of Aspect Ratio 3 And Inline Tail Surfaces written by Warren Jr Gillespie 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.
Stability Of Two Rocket Propelled Models Having Aspect Ratio 5 Unswept Tails On A Long Body For The Mach Number Range Of 1 7 To 2 4
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Author : Reginald R. Lundstrom
language : en
Publisher:
Release Date : 1957
Stability Of Two Rocket Propelled Models Having Aspect Ratio 5 Unswept Tails On A Long Body For The Mach Number Range Of 1 7 To 2 4 written by Reginald R. Lundstrom and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aerodynamics, Supersonic categories.
Two rocket models having cruciform, aspect-ratio-5, unwswept tails and a fineness-ratio-20 fuselage were flight tested over a Mach number range of approximately 1.7 to 2.4. One of the models had cruciform, aspect-ratio-3.4 forward surfaces in line with the tails. The models were given step disturbances by pulse rockets at intervals throughout the Mach number range and stability derivatives were obtained from the measured responses. The roll rates of the models varied from 10 radians per second to 5 radians per second.
Lift Drag And Longitudinal Stability At Mach Numbers From 0 8 To 2 1 Of A Rocket Powered Model Having A Tapered Unswept Wing Of Aspect Ratio 3 And Inline Tail Surfaces
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Author : Warren Jr Gillespie
language : en
Publisher:
Release Date : 1955
Lift Drag And Longitudinal Stability At Mach Numbers From 0 8 To 2 1 Of A Rocket Powered Model Having A Tapered Unswept Wing Of Aspect Ratio 3 And Inline Tail Surfaces written by Warren Jr Gillespie 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.
Results Of Rocket Model Test Of An Airplane Configuration Having An Arrow Wing And Slender Flat Sided Fuselage
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Author : Robert F. Peck
language : en
Publisher:
Release Date : 1956
Results Of Rocket Model Test Of An Airplane Configuration Having An Arrow Wing And Slender Flat Sided Fuselage written by Robert F. Peck and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Aerodynamics, Supersonic categories.
A rocket-propelled model of an airplane configuration having an arrow wing with 55 degree leading-edge sweep and a flat-sided fuselage mounting swept horizontal and vertical tails has been tested through use of the pulse-control technique at Mach numbers between 1.0 and 2.3. Results are presented from an investigation of longitudinal trim, lift, stability, drag, lateral force, thrust, and jet effects.
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.
Effect Of Forebody Wing Strakes On Enhancing Performance Of A Typical Body Wing Tail Missile Configuration At Mach 2 0
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Author : Pamela K. Alstott
language : en
Publisher:
Release Date : 1980
Effect Of Forebody Wing Strakes On Enhancing Performance Of A Typical Body Wing Tail Missile Configuration At Mach 2 0 written by Pamela K. Alstott and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with Aerodynamics, Supersonic categories.
The addition of forebody strakes to aircraft configurations have shown significant improvement in aircraft performance at moderate-to-high angles-of-attack for subsonic nd transonic speeds. This research project investigates the effect of strakes on missile type body-wing-tail configurations at supersonic speeds by conducting a (1) literature survey of related existing data and design methods and (2) analyzing a new set of wind tunnel data on a body-wing-tail missile configuration with added forebody strakes at Mach 2.0. Findings from the literature survey are presented. Analysis of the wind tunnel data reveals that added forebody strakes do not significantly improve missile performance at Mach 2.0 and angles-of-attack up to 20 degrees for the configuration tested. (Author).