Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part 2 Parametric Configuration Development And Evaluation
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Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part 2 Parametric Configuration Development And Evaluation
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Author :
language : en
Publisher:
Release Date : 1968
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part 2 Parametric Configuration Development And Evaluation written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with categories.
The derivation of two volumetric efficient high L/D entry vehicles is described. Parametric trades in the areas of aerodynamics and aerothermodynamics are discussed and selected parameters are identified. Alternate modes of vehicle recovery are described and the effect on vehicle design determined. The evolution of the FDL-5 configuration selected for wind tunnel testing is described through the presentation of a series of intermediate configurations.
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part 5 Vehicle Design
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Author :
language : en
Publisher:
Release Date : 1968
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part 5 Vehicle Design written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with categories.
A parametric analysis of a broad spectrum of thermostructural concepts is presented. A complete structural concept for the 35-foot entry test vehicle using the FDL-5 configuration is defined. Subsystems for the entry test vehicle are selected. A weight breakdown and a weight summary for the test vehicle are presented.
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part I Summary
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Author :
language : en
Publisher:
Release Date : 1968
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part I Summary written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with categories.
Conceptual design and experimental wind tunnel testing of unmanned entry research vehicles having high hypersonic lift/drag ratio and high volume are described. Analytic parametric data are presented for two lifting body classes designated HLD-35 and FDL-5. The FDL-5 is a unique configuration which is aerodynamically stabilized without outboard fins. Experimental aerodynamic and heat transfer fata from the Arnold Engineering Development Center Wind Tunnels A, B, C, and F are compared with analytic data for the FDL-5. Candidate structure and subsystems are selected for performing unmanned hypersonic research with the vehicle. (Author).
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft
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Author : F. L. Guard
language : en
Publisher:
Release Date : 1968
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft written by F. L. Guard and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with Aerodynamics, Hypersonic categories.
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part 3 Aerodynamics
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Author :
language : en
Publisher:
Release Date : 1968
Preliminary Design And Experimental Investigation Of The Fdl 5a Unmanned High L D Spacecraft Part 3 Aerodynamics written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with categories.
The aerodynamic wind tunnel test program for the FDL-5 configuration is described in this Part III. The description includes the models, test facilities, data reduction and presentation, and the test schedules. A complete presentation of the aerodynamic test data is provided. The data include six component force and moment data, pressure data, and photographic data for the Mach number range between 1.5 to 20. Correlations between the data and appropriate theories are presented. The overall aerodynamic characteristics of the FDL-5 configuration are defined.