Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 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 Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 PDF full book. Access full book title Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 by Earl D. Knechtel. Download full books in PDF and EPUB format.
Author: Earl D. Knechtel
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Get Book Here
Book Description
An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stability characteristics of a 53 and a 63 degree sweptback wing-body combination. Both models were tested with flat and abruptly drooped wing tips. The 63 degree wing was also tested with a curved drooped tip. In addition, the combined effects of wing fences and extended leading-edge flaps were investigated. The results showed that abrupt droop of the outer 40 percent of the basic 53 degree wing improved the stability characteristics of the model. For the 63 degree swept wing, curved droop caused slight beneficial effects on the stability, whereas abrupt droop caused adverse effects. In general, the most favorable stability characteristics were obtained for either flat or abruptly drooped wings with fences and extended leading-edge flaps.
Author: Earl D. Knechtel
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
Get Book Here
Book Description
An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stability characteristics of a 53 and a 63 degree sweptback wing-body combination. Both models were tested with flat and abruptly drooped wing tips. The 63 degree wing was also tested with a curved drooped tip. In addition, the combined effects of wing fences and extended leading-edge flaps were investigated. The results showed that abrupt droop of the outer 40 percent of the basic 53 degree wing improved the stability characteristics of the model. For the 63 degree swept wing, curved droop caused slight beneficial effects on the stability, whereas abrupt droop caused adverse effects. In general, the most favorable stability characteristics were obtained for either flat or abruptly drooped wings with fences and extended leading-edge flaps.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1492
Get Book Here
Book Description
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 2300
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
Get Book Here
Book Description
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 2084
Get Book Here
Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1812
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1032
Get Book Here
Book Description
Author: Earl D. Knechtel
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
Get Book Here
Book Description
An experimental investigation was conducted to assess the effects of sweep and taper ratio on the longitudinal characteristics of a wing-body combination at Mach numbers from 0.6 to 14 and for a Reynolds number of 1,500,000. The wings were 3 percent thick and of aspect ratio 3. Leading-edge sweep was varied from 19.1 to 53.1 degrees at a constant taper ratio of 0.4, and taper ratio was varied from 0 to 0.5 at a constant sweep angle of 53.1 degrees.
