Summary of Transformation Equations and Equations of Motion Used in Free-flight and Wind-tunnel Data Reduction and Analysis

Summary of Transformation Equations and Equations of Motion Used in Free-flight and Wind-tunnel Data Reduction and Analysis PDF Author: Thomas G. Gainer
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 148

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Summary of Transformation Equations and Equations of Motion Used in Free Flight and Wind Tunnel Data Reduction and Analysis

Summary of Transformation Equations and Equations of Motion Used in Free Flight and Wind Tunnel Data Reduction and Analysis PDF Author: Thomas G. Gainer
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 140

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Summary of Transformation Equations and Equations of Motion Used in Free-flight and Wind-tunnel Data Reduction and Analysis

Summary of Transformation Equations and Equations of Motion Used in Free-flight and Wind-tunnel Data Reduction and Analysis PDF Author: Thomas G. Gainer
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 148

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NASA Technical Memorandum

NASA Technical Memorandum PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 32

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1572

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Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments

Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments PDF Author: Timothy R. Moes
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 98

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A maximum-likelihood output-error parameter estimation technique is used to obtain stability and control derivatives for the NASA Dryden Flight Research Center SR-71A airplane and for configurations that include experiments externally mounted to the top of the fuselage. This research is being done as part of the envelope clearance for the new experiment configurations. Flight data are obtained at speeds ranging from Mach 0.4 to Mach 3.0, with an extensive amount of test points at approximately Mach 1.0. Pilot-input pitch and yaw-roll doublets are used to obtain the data. This report defines the parameter estimation technique used, presents stability and control derivative results, and compares the derivatives for the three configurations tested. The experimental configurations studied generally show acceptable stability, control, trim, and handling qualities throughout the Mach regimes tested.

Comparison of Wind Velocity in Thunderstorms Determined from Measurements by a Ground-based Doppler Radar and an F-106B Airplane

Comparison of Wind Velocity in Thunderstorms Determined from Measurements by a Ground-based Doppler Radar and an F-106B Airplane PDF Author: J. W. Usry
Publisher:
ISBN:
Category : Aeronautics in meteorology
Languages : en
Pages : 44

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NASA Technical Paper

NASA Technical Paper PDF Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 42

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NASA Technical Paper

NASA Technical Paper PDF Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 380

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NASA Technical Note

NASA Technical Note PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 492

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NASA Reference Publication

NASA Reference Publication PDF Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 636

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