A Tabulation of Helicopter Rotor-blade Differential Pressures, Stresses, and Motions as Measured in Flight PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download A Tabulation of Helicopter Rotor-blade Differential Pressures, Stresses, and Motions as Measured in Flight PDF full book. Access full book title A Tabulation of Helicopter Rotor-blade Differential Pressures, Stresses, and Motions as Measured in Flight by James Scheiman. Download full books in PDF and EPUB format.
Author: James Scheiman
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 700
Get Book Here
Book Description
Author: James Scheiman
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 704
Get Book Here
Book Description
Author: James Scheiman
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: James Scheiman
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 700
Get Book Here
Book Description
Author: James Scheiman
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 58
Get Book Here
Book Description
Author: Francisco J. Fernandez
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 32
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 712
Get Book Here
Book Description
Author: Robert J. Tapscott
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 692
Get Book Here
Book Description
Theoretically derived charts showing steady-state and first- and second-harmonic flapping coefficients are presented for helicopter rotors having hinged rectangular blades with a linear twist of 0, -8, and -16 degrees. The charts, showing the rotor flapping coefficients for combinations of inflow ratio and blade pitch angle, are presented for tip-speed ratios ranging from 0.05 to 0.50.
Author: John D. Berry
Publisher:
ISBN:
Category : Rotors (Helicopters)
Languages : en
Pages : 54
Get Book Here
Book Description
A test to determine the performance differences between the 27-percent-scale models of two rotors for the U.S. Army AH-64 helicopter was conducted in the Langley 14- by 22-Foot Subsonic Tunnel. One rotor, referred to as the baseline rotor, simulated the geometry and dynamic characteristics of the production baseline rotor, and the other rotor, referred to as the advanced rotor, was designed to have improved hover performance. During the performance test, the dynamic pitch-link forces and blade bending and torsion moments were also measured. Dynamic data from the forward flight investigation have been reduced and are presented herein. The advanced blade set was designed to have dynamic characteristics similar to those of the baseline rotor so that test conditions would not be limited by potential rotor instability and blade resonances and so that the measured performance increments could be considered to be due purely to aerodynamic causes. Data show consistent trends with advance ratio for both blade sets with generally higher oscillatory loads occurring for the advanced blade set when compared with the baseline blade set.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
Get Book Here
Book Description
Author: Richard R. Pruyn
Publisher:
ISBN:
Category :
Languages : en
Pages : 285
Get Book Here
Book Description
The report describes and evaluates the results of an extensive program to measure the dynamic effects of flight on a tandem rotor helicopter. The flight test results are reviewed and then compared with theoretical predictions and with other flight test data. The airloads measurements from this program are similar to those of other flight test programs, with one major exception: single lifting-rotor helicopter data differ from the forward rotor data of a tandem. The aft rotor apparently produces an upwash which gives an increase in the airloads on the inboard region of the forward rotor. This effect results in an airload distribution that is similar to that which would be obtained with an increased blade twist of the forward rotor. For most longitudinal cyclic trim settings, the oscillations of the airloads of both tandem rotors tend to be similar to those of a single rotor, with intrarotor tip vortex intersections causing the predominant disturbances. Longitudinal cyclic trim settings can be obtained experimentally with the tandem helicopter which cause large airload pressure oscillations due to the intersection of forward rotor blade vortexes by the aft rotor blades. These pressure oscillations occur rapidly and do not appear to increase blade stresses, rotor shaft loads, or airframe vibration. (Author).
