A Flight Investigation of Performance and Loads for a Helicopter with NLR-1T Main-rotor Blade Sections 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 Flight Investigation of Performance and Loads for a Helicopter with NLR-1T Main-rotor Blade Sections PDF full book. Access full book title A Flight Investigation of Performance and Loads for a Helicopter with NLR-1T Main-rotor Blade Sections by . Download full books in PDF and EPUB format.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 182
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 182
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 186
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 500
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 554
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 252
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 772
Get Book Here
Book Description
Author: Jeffrey L. Cross
Publisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 472
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 62
Get Book Here
Book Description
The loading of an airfoil during dynamic stall is examined in terms of the augmented lift and the associated penalties in pitching moment and drag. It is shown that once stall occurs and a leading-edge vortex is shed from the airfoil there is a unique relationship between the augmented lift, the negative pitching moment, and the increase in drag. This relationship, referred to here as the dynamic stall function, shows limited sensitivity to effects such as the airfoil section profile and Mach number, and appears to be independent of such parameters as Reynolds number, reduced frequency, and blade sweep. For single-element airfoils there is little that can be done to improve rotorcraft maneuverability except to provide good static clmax characteristics and the chord or blade number that is required to provide the necessary rotor thrust. However, multi-element airfoils or airfoils with variable geometry features can provide augmented lift in some cases that exceeds that available from a single-element airfoil. The dynamic stall function is shown to be a useful tool for the evaluation of both measured and calculated dynamic stall characteristics of singleelement, multi-element, and variable geometry airfoils.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 252
Get Book Here
Book Description
