A Correlation Between Flight-determined Longitudinal and Lateral Derivatives and Wind Tunnel Data for the Pilatus PC 9/A Training Aircraft in Approach and Departure Configurations PDF Download
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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 40
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Book Description
A series of flight tests were conducted on the PC 9/A aircraft, A23-045, at the Royal Australian Air Force's Aircraft Research and Development Unit. System identification techniques were applied to the data obtained from these flight tests to determine the stability and control derivatives of the aircraft. The longitudinal and lateral results for the aircraft in approach and departure configurations are presented in this report and comparisons are made with wind tunnel estimates.
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 40
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Book Description
A series of flight tests were conducted on the PC 9/A aircraft, A23-045, at the Royal Australian Air Force's Aircraft Research and Development Unit. System identification techniques were applied to the data obtained from these flight tests to determine the stability and control derivatives of the aircraft. The longitudinal and lateral results for the aircraft in approach and departure configurations are presented in this report and comparisons are made with wind tunnel estimates.
Author: Defence Science and Technology Organisation
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
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Book Description
A series of flight tests were conducted on the PC 9/A aircraft, A23-045, at the Royal Australian Air Force's Aircraft Research and Development Unit. System identification techniques were applied to the data obtained from these flight tests to determine the stability and control derivatives of the aircraft. The longitudinal results for the aircraft in cruise configuration are presented in this report and comparisons are made with empirical and ground based estimates.
Author: Defence Science and Technology Organisation (Australia)
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
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Book Description
A series of flight tests were conducted on the PC 9/A aircraft, A23-045, at the Royal Australian Air Force's Aircraft Research and Development Unit. System identification techniques were applied to the data obtained from these flight tests to determine the stability and control derivatives of the aircraft. The lateral results for the aircraft in cruise configuration are presented in this report and comparisons are made with empirical and ground based estimates.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 72
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Book Description
Author:
Publisher:
ISBN:
Category : Wool industry
Languages : en
Pages : 12
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Book Description
Author: James J. Donegan
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 40
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Book Description
A method is presented for obtaining the over-all longitudinal-stability coefficients and frequency response of an aircraft from an analysis of arbitrary maneuvers in which simple instrumentation is used. Although the method presented deals entirely with the aircraft, it is equally applicable to other problems which can be expressed by second-order differential equations.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 654
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
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Book Description
Author: James L. Williams
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
A parameter-estimation algorithm was used to extract the longitudinal aerodynamic derivatives from flight data for the XC-142A airplane in a cruise condition. The flight data were the response to a tail-plane doublet input. Results of this study showed that a set of derivatives were determined which yielded a calculated aircraft response in close agreement with the measured response. This calculated response was in much closer agreement with the flight data than the response obtained by using derivatives which were calculated from empirical methods. There were large differences between some of the important derivatives extracted from flight data and those calculated from empirical methods. The reasons for these differences were not identified.
Author: G. R. Casteel
Publisher:
ISBN:
Category : Flight control
Languages : en
Pages : 224
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Book Description
The general objective was to collect and analyze aerodynamic stability and control data for the XV-4B, XV-5A, and P-1127 VTOL configurations. Correlation and analysis of existing model data were made to investigate hover and transition characteristics. Particular emphasis was placed on the aerodynamic power effects, sometimes referred to as interference effects. Other areas of investigation were sometimes referred to as interference effects. Other areas of investigation were nondimensional coefficients used to present VTOL data and wind tunnel test techniques. Wind tunnel tests were conducted using an inlet only model and a jet only model to investigate special test and analysis problems for these components. The agreement between different sets of XV-4B model data was, in general, found to be poor. However, the nondimensional coefficients used by Lockheed to reduce to XV-4B model data appear to be valid parameters for this category of VTOL airplane. The jet entrainment flow was shown by experiment to be the primary cause of the XV-4B power effects, and the XV-4B jet path was experimentally and theoretically determined.
