V-STOL Ejector Short Diffuser Study 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 V-STOL Ejector Short Diffuser Study PDF full book. Access full book title V-STOL Ejector Short Diffuser Study by R. M. O'Donnell. Download full books in PDF and EPUB format.
Author: R. M. O'Donnell
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Get Book Here
Book Description
Development of thrust augmenting ejectors has produced ejector/diffuser configurations capable of achieving the high levels of thrust augmentation necessary for VTOL aircraft propulsion requirements. Experimental testing has shown that thrust augmenting ejectors can be made more compact by reducing diffuser length with active diffusion boundary layer control employing the Antiseparation Tailored Contour (ATC). Thrust augmentation and internal flow measurements were determined in compact high performance thrust augmentors with various length diffusers. The short ATC/diffusers tested showed significant improvements when compared to previous ejector diffusers. Measured thrust augmentation ratios with an optimum short ATC/diffuser were 10% greater than those with an equivalent straight wall diffuser. Length reductions of 36% were indicated for nominal augmentation ratios of 1.7. The important factors which influence the design and operation of compact thrust augmentor ejector/diffusers have been defined. (Author).
Author: R. M. O'Donnell
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Get Book Here
Book Description
Development of thrust augmenting ejectors has produced ejector/diffuser configurations capable of achieving the high levels of thrust augmentation necessary for VTOL aircraft propulsion requirements. Experimental testing has shown that thrust augmenting ejectors can be made more compact by reducing diffuser length with active diffusion boundary layer control employing the Antiseparation Tailored Contour (ATC). Thrust augmentation and internal flow measurements were determined in compact high performance thrust augmentors with various length diffusers. The short ATC/diffusers tested showed significant improvements when compared to previous ejector diffusers. Measured thrust augmentation ratios with an optimum short ATC/diffuser were 10% greater than those with an equivalent straight wall diffuser. Length reductions of 36% were indicated for nominal augmentation ratios of 1.7. The important factors which influence the design and operation of compact thrust augmentor ejector/diffusers have been defined. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 524
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
Get Book Here
Book Description
Author: Walter Z. Collings
Publisher:
ISBN:
Category : Aeronautics, Military
Languages : en
Pages : 212
Get Book Here
Book Description
Author: David G. Koenig
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Get Book Here
Book Description
Ames Research Center, NASA, has been active in several programs which have the objectives of learning to both predict thrusting ejector performance and to package the ejector in tactical aircraft. The Ames 40-by 80-foot Wind Tunnel has been used to evaluate the deHavilland fuselage ejector at large-scale and this wind tunnel and the newer 80- by 120-foot will be used in future programs. These programs will include: (a) the improvement of the fuselage ejector performance; (b) its application to tactical aircraft design through full-scale testing; (c) possibly, the application of the short (Alperin) diffuser to tactical aircraft; and (d) evaluation of new ejector concepts. To take advantage of the size, the objectives of these investigations will focus on the establishment of a well documented data base and evaluating packaging problems - from seal door design to duct losses. The advantage of the new 80- by 120-foot Wind Tunnel will be to allow the use of 15,000 lb (+) engines for propulsion, for singe or two engine configurations, at moderate airspeeds, for larger aircraft. The ejector designs tested will be continually compared with that of other V/STOL designs in the large-scale testing phase.
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages : 792
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 794
Get Book Here
Book Description
Author: Bruce Lowell Storms
Publisher:
ISBN:
Category : Ejector pumps
Languages : en
Pages : 140
Get Book Here
Book Description
