Book Description
The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
Author : Albert G. Few
Publisher :
Page : 80 pages
File Size : 46,30 MB
Release : 1954
Category : Airplanes
ISBN :
The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
Author : Albert G. Few
Publisher :
Page : 62 pages
File Size : 41,44 MB
Release : 1957
Category : Airplanes
ISBN :
The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
Author : Kenneth W. Goodson
Publisher :
Page : 64 pages
File Size : 26,12 MB
Release : 1961
Category : Stability of airplanes, Longitudinal
ISBN :
An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The basic aspect-ratio-4.00 wing had a zero taper and an unswept 0.80 chord line. Several aspect-ratio modifications to the basic wing were made by clipping off portions of the wing tips. The complete model was tested with a chord-plane tail, a T-tail, and a biplane tail (combined T-tail and chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The data show that, when reduced to the same static margin, all the tail configurations tested on the model provided fairly good stability characteristics, the biplane tail giving the best overall characteristics as regards pitching-moment linearity. Changes in static margin at zero lift coefficient with Mach number were small for the model with these tails over the Mach number range investigated.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : pages
File Size : 46,55 MB
Release : 1957
Category : Aeronautics
ISBN :
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 388 pages
File Size : 23,42 MB
Release : 1959
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 1274 pages
File Size : 34,55 MB
Release : 1961
Category : Government publications
ISBN :
Author :
Publisher :
Page : 818 pages
File Size : 19,5 MB
Release : 1954
Category : Aeronautics
ISBN :
Author : F. B. Gustafson
Publisher :
Page : 720 pages
File Size : 50,99 MB
Release : 1957
Category : Aeronautics
ISBN :
Part 1 of this report presents a brief review of methods available to the helicopter designer for obtaining desired stability characteristics by modifications to the airframe design. The discussion is based on modifications made during the establishment of flying-qualities criteria and includes sample results of theoretical studies of additional methods. The conclusion is reached that it is now feasible to utilize combinations of methods whereby stability-parameter values are realized which in turn provide the desired stability characteristics. Part 2 reviews some of the methods of predicting rotor stability derivatives. The procedures by which these rotor derivatives are employed to estimate helicopter stability characteristics have been summarized.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 508 pages
File Size : 22,9 MB
Release : 1954
Category : Aeronautics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 480 pages
File Size : 24,61 MB
Release : 1957
Category : Aeronautics
ISBN :