Studies of STOL aircraft show that relatively high maximum lift-coefficients and large increases in lift due to power are within present state of art; with these lift characteristics, approach speeds of order of 60 knots for aircraft of moderate wing loading can be realized; full advantage of STOL performance of aircraft may not be realized on routine operational basis, however, without some form of damping augmentation system because of lateral-directional handling considerations, particularly for large aircraft operating under instrument flight conditions; satisfactory characteristics can be obtained by use of only servodriven rudder. (See also AGARD -- Report 504 June 1965 36 p)
Stability and control considerations for STOL aircraft
Can Aeronautics Space J
Canadian Aeronautics and Space Journal ; 12 , n 5
1966
12 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Stability and control considerations for STOL AIRCRAFT.
NTRS | 1966
|Stability and control considerations for STOL AIRCRAFT
AIAA | 1965
|Stability and control considerations for STOL AIRCRAFT.
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