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Experimental And Numerical Optimization Of A High Lift System To Improve Low Speed Performance Stability And Control Of An Arrow Wing Supersonic Transport
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Book Synopsis Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Transport by : David Edgar Hahne
Download or read book Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Transport written by David Edgar Hahne and published by . This book was released on 1999 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720517665 Total Pages :86 pages Book Rating :4.5/5 (176 download)
Book Synopsis Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Transport by : National Aeronautics and Space Administration (NASA)
Download or read book Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Transport written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was performed to evaluate leading-and trailing-edge flap deflections for optimal aerodynamic performance of a High-Speed Civil Transport concept during takeoff and approach-to-landing conditions. The configuration used for this study was designed by the Douglas Aircraft Company during the 1970's. A 0.1-scale model of this configuration was tested in the Langley 30- by 60-Foot Tunnel with both the original leading-edge flap system and a new leading-edge flap system, which was designed with modem computational flow analysis and optimization tools. Leading-and trailing-edge flap deflections were generated for the original and modified leading-edge flap systems with the computational flow analysis and optimization tools. Although wind tunnel data indicated improvements in aerodynamic performance for the analytically derived flap deflections for both leading-edge flap systems, perturbations of the analytically derived leading-edge flap deflections yielded significant additional improvements in aerodynamic performance. In addition to the aerodynamic performance optimization testing, stability and control data were also obtained. An evaluation of the crosswind landing capability of the aircraft configuration revealed that insufficient lateral control existed as a result of high levels of lateral stability. Deflection of the leading-and trailing-edge flaps improved the crosswind landing capability of the vehicle considerably; however, additional improvements are required.Hahne, David E. and Glaab, Louis J.Langley Research CenterNUMERICAL ANALYSIS; EXPERIMENTATION; DATA ACQUISITION; LIFT DEVICES; LEADING EDGE FLAPS; LATERAL CONTROL; LATERAL STABILITY; ANALYSIS (MATHEMATICS); PERFORMANCE TESTS; AERODYNAMIC CHARACTERISTICS; AIRCRAFT CONFIGURATIONS; ARROW WINGS; DEFLECTION; DOUGLAS AIRCRAFT; FLAPPING; HIGH SPEED; LOW SPEED; MODEMS; PERTURBATION; SCALE MODELS; SUPERSONIC TRANSPORTS
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781723950759 Total Pages :88 pages Book Rating :4.9/5 (57 download)
Book Synopsis Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Tra by : National Aeronautics and Space Adm Nasa
Download or read book Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Tra written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-23 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was performed to evaluate leading-and trailing-edge flap deflections for optimal aerodynamic performance of a High-Speed Civil Transport concept during takeoff and approach-to-landing conditions. The configuration used for this study was designed by the Douglas Aircraft Company during the 1970's. A 0.1-scale model of this configuration was tested in the Langley 30- by 60-Foot Tunnel with both the original leading-edge flap system and a new leading-edge flap system, which was designed with modem computational flow analysis and optimization tools. Leading-and trailing-edge flap deflections were generated for the original and modified leading-edge flap systems with the computational flow analysis and optimization tools. Although wind tunnel data indicated improvements in aerodynamic performance for the analytically derived flap deflections for both leading-edge flap systems, perturbations of the analytically derived leading-edge flap deflections yielded significant additional improvements in aerodynamic performance. In addition to the aerodynamic performance optimization testing, stability and control data were also obtained. An evaluation of the crosswind landing capability of the aircraft configuration revealed that insufficient lateral control existed as a result of high levels of lateral stability. Deflection of the leading-and trailing-edge flaps improved the crosswind landing capability of the vehicle considerably; however, additional improvements are required.Hahne, David E. and Glaab, Louis J.Langley Research CenterNUMERICAL ANALYSIS; EXPERIMENTATION; DATA ACQUISITION; LIFT DEVICES; LEADING EDGE FLAPS; LATERAL CONTROL; LATERAL STABILITY; ANALYSIS (MATHEMATICS); PERFORMANCE TESTS; AERODYNAMIC CHARACTERISTICS; AIRCRAFT CONFIGURATIONS; ARROW WINGS; DEFLECTION; DOUGLAS AIRCRAFT; FLAPPING; HIGH SPEED; LOW SPEED; MODEMS; PERTURBATION; SCALE MODELS; SUPERSONIC TRANSPORTS
Book Synopsis NASA Langley Scientific and Technical Information Output: 1999 by :
Download or read book NASA Langley Scientific and Technical Information Output: 1999 written by and published by . This book was released on 2000 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low Speed Aerodynamic Characteristics of a Modified Arrow-wing Supersonic Transport Configuration with High Lift Devices by :
Download or read book Low Speed Aerodynamic Characteristics of a Modified Arrow-wing Supersonic Transport Configuration with High Lift Devices written by and published by . This book was released on 1964 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Piloted Fixed-base Simulator Study of Low-speed Flight Characteristics of an Arrow-wing Supersonic Transport Design by : William D. Grantham
Download or read book A Piloted Fixed-base Simulator Study of Low-speed Flight Characteristics of an Arrow-wing Supersonic Transport Design written by William D. Grantham and published by . This book was released on 1968 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Effects of High-lift Devices on the Aerodynamic Characteristics of a Supersonic Transport Model with Outboard Tails by : William C. Sleeman
Download or read book Low-speed Effects of High-lift Devices on the Aerodynamic Characteristics of a Supersonic Transport Model with Outboard Tails written by William C. Sleeman and published by . This book was released on 1963 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Leading-edge Contour and Vertical-tail Configuration on the Low-speed Stability Characteristics of a Supersonic Transport Model Having a Highly-swept Arrow Wing by :
Download or read book Effect of Leading-edge Contour and Vertical-tail Configuration on the Low-speed Stability Characteristics of a Supersonic Transport Model Having a Highly-swept Arrow Wing written by and published by . This book was released on 1978 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length by : Carlton S. James
Download or read book Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length written by Carlton S. James and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An aircraft configuration, previously conceived as a means to achieve favorable aerodynamic stability characteristics., high lift-drag ratio, and low heating rates at high supersonic speeds., was modified in an attempt to increase further the lift-drag ratio without adversely affecting the other desirable characteristics. The original configuration consisted of three identical triangular wing panels symmetrically disposed about an ogive-cylinder body equal in length to the root chord of the panels. This configuration was modified by altering the angular disposition of the wing panels, by reducing the area of the panel forming the vertical fin, and by reshaping the body to produce interference lift. Six-component force and moment tests of the modified configuration at combined angles of attack and sideslip were made at a Mach number of 3.3 and a Reynolds number of 5.46 million. A maximum lift-drag ratio of 6.65 (excluding base drag) was measured at a lift coefficient of 0.100 and an angle of attack of 3.60. The lift-drag ratio remained greater than 3 up to lift coefficient of 0.35. Performance estimates, which predicted a maximum lift-drag ratio for the modified configuration 27 percent greater than that of the original configuration, agreed well with experiment. The modified configuration exhibited favorable static stability characteristics within the test range. Longitudinal and directional centers of pressure were slightly aft of the respective centroids of projected plan-form and side area.
Book Synopsis Low-speed Wind-tunnel Investigation of a Large-scale Advanced Arrow-wing Supersonic Transport Configuration with Engines Mounted Above Wings for Upper-surface Blowing by : James P. Shivers
Download or read book Low-speed Wind-tunnel Investigation of a Large-scale Advanced Arrow-wing Supersonic Transport Configuration with Engines Mounted Above Wings for Upper-surface Blowing written by James P. Shivers and published by . This book was released on 1976 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 836 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios by : Richard T. Whitcomb
Download or read book A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Book Synopsis High-lift Characteristics of a Variable-sweep Supersonic Transport Model with a Blended Engine-fuselage and Engine-mounted Horizontal Tails by : Vernard E. Lockwood
Download or read book High-lift Characteristics of a Variable-sweep Supersonic Transport Model with a Blended Engine-fuselage and Engine-mounted Horizontal Tails written by Vernard E. Lockwood and published by . This book was released on 1966 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Low-speed Longitudinal Stability Improvement Study on a Highly Swept Supersonic Transport Configuration by :
Download or read book A Low-speed Longitudinal Stability Improvement Study on a Highly Swept Supersonic Transport Configuration written by and published by . This book was released on 1965 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Scientific and Technical Publications by :
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1987 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds by : A. J. Eggers (Jr.)
Download or read book Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds written by A. J. Eggers (Jr.) and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The problem of designing an aircraft which will develop high lift-drag ratios in flight at high supersonic speeds is attacked using the elementary principle that the components of the aircraft should be individually and collectively arranged to impart the maximum downward and the minimum forward momentum to the surrounding air. This principle in conjunction with other practical considerations of hypersonic flight leads to the study of configurations for which the body is situated entirely below the wing; that is, flat-top wing-body combinations. Theory indicates that sensibly complete aircraft of this type can be designed to develop lift-drag ratios well in excess of 6.
Book Synopsis Low-speed Aerodynamic Characteristics of a Proposed Supersonic Transport Configuration Having a 53.13 Deg Delta Wing and Forward and Aft Controls in Combination by :
Download or read book Low-speed Aerodynamic Characteristics of a Proposed Supersonic Transport Configuration Having a 53.13 Deg Delta Wing and Forward and Aft Controls in Combination written by and published by . This book was released on 1963 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
