Elevator Hinge Moment Design of N219-B12

Mochamad Dady Ma'mun and Muhammad Fajar and Yitno Dwi Astoto and Wuryadi Kundarta and Junitu Tikupasang (2015) Elevator Hinge Moment Design of N219-B12. Proceedings International Seminar of Aerospace Science and Technology, 2015. pp. 68-75.

[img]
Preview
Text
Prosiding_Mochamad Dady Ma'mun dkk_Pustekbang_2015.pdf

Download (280kB) | Preview

Abstract

The elevator hinge moment of N219-B12 was investigated based on the design criteria corresponded to the critical flight conditions for Stability and Control point of view. The criteria were adopted from Boeing criteria in its hinge moment design [1]. This criteria was not the only criteria in hinge moment design of aircraft, however, this criteria was implemented on N250-PA1 aircraft on its hinge moment design phase. In order to find the elevator hinge moment coefficients data, the wind tunnel testing was conducted in open jet type of subsonic wind tunnel LAPAN low speed tunnel. The model was 1: 6.3 scaled of an isolated half model of port horizontal tail plane (HTP) N219-B12 aircraft. The investigations showed that N219-B12 aircraft needed the servo tab to reduce the elevator stick force in order to meet the regulation of CASR 23 (commuter category aircraft) in its design. In addition, the servo tab and trim tab analyze were also described in this paper.

Item Type: Article
Additional Information: ISBN 978-602-71833-1-5
Uncontrolled Keywords: Wind Tunnel Test, Elevator Hinge Moment, Servo Tab, Trim Tab
Subjects: Teknologi Penerbangan dan Antariksa > Penelitian, Pengembangan, Perekayasaan, dan Pemanfaatan > Teknologi Aeronautika
Divisions: Deputi Teknologi Penerbangan Dan Antariksa > Pusat Teknologi Penerbangan
Depositing User: Dinar Indrasasi
Date Deposited: 17 Mar 2021 13:50
Last Modified: 21 Sep 2021 23:04
URI: http://repositori.lapan.go.id/id/eprint/461

Actions (login required)

View Item View Item