• Title/Summary/Keyword: Turboprop aircraft

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Analysis and Calibration of Propeller Power Effect for Turboprop Aircraft (터보프롭 항공기의 프로펠러 파워효과 해석 및 보정)

  • Park, Youngmin;Chung, Jindeog
    • Journal of Aerospace System Engineering
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    • v.9 no.4
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    • pp.62-66
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    • 2015
  • During the conceptual design of turboprop aircraft, the power effect driven from rotating propeller is typically obtained from empirical data. In the present paper, propeller power effect was obtained by using unsteady three-dimensional Navier-Stokes solver with $k-{\omega}$ turbulence model for the accurate prediction of turboprop aircraft performance. In order to simulate the relative motion between propeller and fuselage, unsteady sliding mesh method was used. During simulation, three flow conditions such as climb, cruise and descending flight were selected considering the flight envelop of the real turboprop aircraft. For the correction of aerodynamic coefficients, the thrust effect of engine exhaust gas was included based on the engine manufacturer's data. Using the computational results, the correction table for the aerodynamic coefficient of turboprop aircraft was suggested for the performance analysis of turboprop aircraft.

Performance Analysis of Turboprop Aircraft Propulsion System by using Gasturb (Gasturb를 이용한 터보프롭 항공기 추진시스템 성능해석)

  • Choi, Won;Jeong, In-Myon;You, Jae-Ho;Kim, Ji-Hong;Lee, Il-Woo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.371-377
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    • 2009
  • The propulsion system of turboprop has been rarely used in the large aircraft due to the limitation of the maximum velocity of the propeller, the power limitation by the reduction gear, etc. Recently, the demand on turboprop aircraft continues to increase because of economical efficiency and environmental factors. In this paper, turboprop propulsion system which is composed of a Pratt & Whitney 127F turboprop engine and a Hamilton Standard 568F propeller was modeled by using the Gasturb11 software. The result of the performance analysis on this propulsion system model showed that the propulsion system model was evaluated to have been successfully builded.

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CFD Analysis of Aerodynamic Characteristics of Regional Turboprop Aircraft Propeller (중형 터보프롭 항공기급 프로펠러 공력특성 전산해석)

  • Choi, W.;Choi, J.S.;Jung, I.M.;Kim, J.H.;Lee, I.W.;Han, S.H.;Won, Y.S.
    • 한국전산유체공학회:학술대회논문집
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    • 2011.05a
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    • pp.447-452
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    • 2011
  • Propeller shall have high efficiency and improved aerodynamic characteristics to get the thru5t to fly at high speed for the Regional turboprop aircraft. That is way Clark-Y airfoil which is used to conventional turboprop aircraft propeller is selected as a blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the propeller design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point of Regional turboprop aircraft. The propeller design results indicate that is evaluated to be properly constructed, through analysis of propeller aerodynamic characteristics using the Meshless method and MRF, SM method.

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The Study of Propeller Design and Aerodynamics Characteristics for FAR25 Grade Turboprop Aircraft (FAR25급 터보프롭 항공기 프로펠러 설계 및 공력특성 연구)

  • Choi, Won;Jeong, In-Myon;Kim, Ji-Hong;Lee, Il-Woo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.648-651
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    • 2010
  • Propeller shall have high efficiency and improved aerodynamic characteristics to get the thrust to fly at high speed for the FAR25 turboprop aircraft. That is way Clark-Y airfoil which is used to conventional turboprop aircraft propeller is selected as a blade airfoil. Javaprop program based on the Adkins method is used for aerodynamic design and analysis of propeller, Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. Slipstream displacement don't change and consider a rigid body. High efficiency propeller geometry is generated by varying chord length and pitch angle at design point of FAR25 turboprop aircraft. The propeller design results indicate that could be applied to the FAR25 turboprop aircraft, through analysis of propeller aerodynamic characteristics using the CFD(Computational Fluid Dynamic).

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Tail Sizing of 95-Seat Type Turboprop Aircraft (95인승급 터보프롭 중형항공기 꼬리날개 사이징)

  • Lee, Jangho;Kang, Youngsin;Bae, Hyogil;Lee, Hae-Chang
    • Journal of Aerospace System Engineering
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    • v.7 no.3
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    • pp.15-19
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    • 2013
  • Tail wing is important to designing of civil aircrafts, because it is responsible for aircraft stability and control. Tail wing has a role in aircraft control and makes aircraft fly stably without any pilot control input. Also, designing of tail wing determine trim drag force in whole aircraft. Center of gravity(CG) of aircraft travels with various effects as placement of passenger's seats, location of cargo bay, etc. In designing horizontal tail volume, aircraft CG travel has to be considered to have margin so that it should be sized to provide adequate stability and control for the airplane's entire CG range throughout the flight envelope. Finally, it is essential to have sufficient elevator control to perform stall at forward CG for all flaps down configurations. Such stalls establish the FAR stall speed which airplane take-off and landing performance. This paper deals with the process for tail wing design regarding the aircraft CG travel and results for 95-seat type turboprop aircraft.

Initial Configuration Layout Design for 95-Seat Regional Turboprop Aircraft

  • Hwang, In Seong;Chung, Jindeog;Kang, Wanggu;Lee, Hae-Chang
    • International Journal of Aeronautical and Space Sciences
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    • v.15 no.2
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    • pp.138-145
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    • 2014
  • The initial configuration for 95-seat passenger regional turboprop aircraft, the so called KC950, was designed to meet the market requirements. This paper prescribes the initial design based upon aircraft design guidelines and compared the competitive aircraft configurations after considering the related FAR 25 regulations. More specifically, results of design describe how to select the fuselage cross-sectional area, how to layout the cabin, and how to determine the overall shape and physical dimension of the fuselage. Sizing of wing and empennage areas is estimated using empirical equations and tail volume coefficients in this design. Some design guidelines to determine wing sweep angle, taper ratio, incidence angle and location are also introduced.

Design and Test of an Assembly of Air Intake and Variable Geometry Inertial Separator for a Turboprop Aircraft (터보프롭 항공기용 흡입구 덕트 및 가변형 관성분리기 조립체 설계 및 시험)

  • Kim, Woncheol;Oh, Seonghwan;Lee, Sanghyo;Park, Jonghwa
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.9
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    • pp.714-719
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    • 2013
  • A turboprop aircraft for this study is required to operate at icing condition in order that it performs its given mission. So an air intake system of the turboprop aircraft should be designed and verified not only to provide the maximum possible total pressure at engine inlet at normal flight condition, but also to include an inertial separator which protects Foreign Object Debris (FOD) like ice or snow at icing condition from entering into the engine inlet screen which can cause or lead an catastrophic engine failure like engine flame-out or severe damage. So an air intake assembly incorporating a variable geometry inertial separator has been designed and then CFD/structural analysis for the assembly was performed to see its design results. Then 35% scaled model of the air intake assembly was manufactured and wind tunnel test was done. This paper describes the detailed design results for the aerodynamic design, analysis and wind tunnel testing during the development process of the air intake assembly.

The Design and Analysis of Composite Advanced Propeller Blade for Next Generation Turboprop Aircraft (차세대 터보프롭 항공기용 복합재 최신 프로펠러 설계 및 해석)

  • Choi, Won;Kim, Kwang-Hae;Lee, Won-Joong
    • The KSFM Journal of Fluid Machinery
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    • v.15 no.6
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    • pp.11-17
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    • 2012
  • The one way fluid structure interaction analysis on advanced propeller blade for next generation turboprop aircraft. HS1 airfoil series are selected as a advanced propeller blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point. Blade sweep is designed based on the design mach number and target propulsion efficiency. The aerodynamic characteristics of the designed Advanced propeller were verified by CFD(Computational Fluid Dynamic) and showed the enhanced performance than the conventional propeller. The skin-foam sandwich structural type is adopted for blade. The high stiffness, strength carbon/epoxy composite material is used for the skin and PMI(Polymethacrylimide) is used for the foam. Aerodynamic load is calculated by computational fluid dynamics. Linear static stress analysis is performed by finite element analysis code MSC.NASTRAN in order to investigate the structural safety. The result of structural analysis showed that the design has sufficient structural safety. It was concluded that structural safety assessment should incorporate the off-design points.

Aerodynamic Design and Analysis on 1600kW Class Propeller Blade (1600kW급 프로펠러 블레이드 공력설계 및 해석)

  • Choi, Won;Kim, Kwang-Hae;Won, Young-Su;Lee, Won-Joong
    • The KSFM Journal of Fluid Machinery
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    • v.15 no.3
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    • pp.19-24
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    • 2012
  • Propeller shall have high efficiency and improved aerodynamic characteristics to get the thrust to fly at high speed for the turboprop aircraft. That is way Clark-Y airfoil which is used to conventional 1600kW class aircraft propeller is selected as a blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the propeller design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point of turboprop aircraft. The propeller design results indicate that is evaluated to be properly constructed, through analysis of propeller aerodynamic characteristics using the Meshless method and MRF, SM method.

A study on the control law of automatic rudder trim system for KTX-1 (KTX-1 자동러더트림 장치 제어 법칙에 관한 연구)

  • 박완기;김병수;이재명
    • 제어로봇시스템학회:학술대회논문집
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    • 1997.10a
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    • pp.1647-1650
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    • 1997
  • This paper presents the control law of Automatic Rudder Trim System(ARTS) for the KTX-1. The proposed ARTS is designed mainly t reduce the pilot's work load for trimming in the various conditiions of engine torque. airspeed, and aircraft configuration. The ARTS partially compensates the transient yawing motion due to change of engine power in turboprop aircraft because of the limitation of the actuation speed of the trim motor. In this paper flight test data are analyzed to understand the phenomena and the dynamics of the reversible rudder flight control system is derived. Finally, the control concept and conrtol law of ARTS are described and the characteristics of the ARTS are analyzed through simulation study.

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