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Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics

Author: S M Harmon; Langley Aeronautical Laboratory.; United States. National Advisory Committee for Aeronautics.
Publisher: Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1945.
Series: NACA collection.
Edition/Format:   Print book : National government publication : EnglishView all editions and formats
Summary:
An iteration method is given for determining the longitudinal control characteristics of a flexible horizontal tail. The method permits factors such as the actual spanwise variation of elasticity and the aerodynamic induction effects due to three-dimensional flow to be accounted for to any degree of accuracy appropriate to a particular case. An analysis is included of the effects of horizontal-tail flexibility on  Read more...
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Additional Physical Format: Online version:
Harmon, S.M.
Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics.
Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1945
(OCoLC)857368781
Material Type: Government publication, National government publication, Internet resource
Document Type: Book, Internet Resource
All Authors / Contributors: S M Harmon; Langley Aeronautical Laboratory.; United States. National Advisory Committee for Aeronautics.
OCLC Number: 71296653
Notes: "Report no. L-45."
"Originally issued February 1945 as Advance Confidential Report L5B01."
"Report date February 1945."
"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."
Description: 34, [10] pages : illustrations ; 28 cm
Series Title: NACA collection.
Other Titles: NACA wartime reports
Responsibility: by S.M. Harmon.

Abstract:

An iteration method is given for determining the longitudinal control characteristics of a flexible horizontal tail. The method permits factors such as the actual spanwise variation of elasticity and the aerodynamic induction effects due to three-dimensional flow to be accounted for to any degree of accuracy appropriate to a particular case. An analysis is included of the effects of horizontal-tail flexibility on the tail effectiveness, the hinge-moment characteristics, and the control-force gradients in a dive recovery for two modern fighter airplanes. The effects of variations in speed, altitude, elevator stiffness, and center-of-gravity movements are considered. The result of these calculations for speeds below that at which critical compressibility effects occur indicate for the two airplanes significant effects due to the tail flexibility. It appears that the location of the flexural axis of the stabilizer too far behind the aerodynamic center of the tail may cause excessive control forces in a dive recovery at high speeds.

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