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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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.
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.
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.
Comparison Of Low Lift Drag At Mach Numbers From 0 74 To 1 37 Of Rocket Boosted Models Having Externally Braced Wings And Cantilever Wings
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Author : Waldo L. Dickens
language : en
Publisher:
Release Date : 1957
Comparison Of Low Lift Drag At Mach Numbers From 0 74 To 1 37 Of Rocket Boosted Models Having Externally Braced Wings And Cantilever Wings written by Waldo L. Dickens and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aerofoils categories.
An investigation has been conducted to determine whether the low-lift drag of a rocket-model airplane-like configuration could be reduced at transonic and low supersonic Mach numbers by reducing the wing thickness while external braces were used to provide the necessary bending strength. The investigation consisted of flight training two rocket models having aspect ratio 3.04, unswept braced tapered wings mounted on fuselages with the same fineness ratios and cross-sectional area distributions. Data collected from the flight test of a model having a thicker cantilever wing of the same plan form were compared with data collected in this investigation.
Drag Due To Lift At Mach Numbers Up To 2 0
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Author : Edward C. Polhamus
language : en
Publisher:
Release Date : 1953
Drag Due To Lift At Mach Numbers Up To 2 0 written by Edward C. Polhamus and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Airplanes categories.
Aerodynamic Characteristics At Mach Numbers From 0 50 To 2 96 Of A Supersonic Transport Model With A Variable Sweep High Panel Aspect Ratio Wing
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Author :
language : en
Publisher:
Release Date : 1964
Aerodynamic Characteristics At Mach Numbers From 0 50 To 2 96 Of A Supersonic Transport Model With A Variable Sweep High Panel Aspect Ratio Wing written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with categories.
Longitudinal Stability And Drag Characteristics At Mach Numbers From 0 70 To 1 37 Of Rocket Propelled Models Having A Modified Triangular Wing
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Author : Rowe Jr Chapman
language : en
Publisher:
Release Date : 1952
Longitudinal Stability And Drag Characteristics At Mach Numbers From 0 70 To 1 37 Of Rocket Propelled Models Having A Modified Triangular Wing written by Rowe Jr Chapman 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.
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.
A Rocket Model Investigation Of The Longitudinal Stability Lift And Drag Characteristics Of The Douglas X 3 Configuration With Horizontal Tail Of Aspect Ratio 4 33
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Author : Robert F. Peck
language : en
Publisher:
Release Date : 1953
A Rocket Model Investigation Of The Longitudinal Stability Lift And Drag Characteristics Of The Douglas X 3 Configuration With Horizontal Tail Of Aspect Ratio 4 33 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 1953 with categories.