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  • 1
    Electronic Resource
    Electronic Resource
    DRAG DUE TO LIFT: Concepts for Prediction and Reduction (2001)
    Palo Alto, Calif. : Annual Reviews
    Annual Review of Fluid Mechanics 33 (2001), S. 587-617 
    Details
    ISSN: 0066-4189
    Source: Annual Reviews Electronic Back Volume Collection 1932-2001ff
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Notes: Abstract This article describes some of the fundamental ideas underlying methods for induced-drag prediction and reduction. A review of current analysis and design methods, including their development and common approximations, is followed by a survey of several approaches to lift-dependent drag reduction. Recent concepts for wing planform optimization, highly nonplanar surfaces, and various tip devices may lead to incremental but important gains in aircraft performance. Focusing on relatively high-aspect-ratio subsonic wings, the review suggests that opportunities for new concepts remain, but the greatest challenge lies in their integration with other aspects of the system.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1146/annurev.fluid.33.1.587
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    Paper (German National Licenses)
    Fulltext
  • 2
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    DRAGDUE TOLIFT: Concepts for Prediction and Reduction (2001)
    Annual Reviews
    Details
    Publication Date: 2001-01-01
    Print ISSN: 0066-4189
    Electronic ISSN: 1545-4479
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Annual Reviews
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    PAPER CURRENT
  • 3
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    Computation of induced drag for elliptical and crescent-shaped wings (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 30; 4; p. 446-452.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Preliminary design optimization of joined-wing aircraft (1990)
    In:  CASI
    Details
    Publication Date: 2004-12-04
    Description: The joined wing is an innovative aircraft configuration that has a its tail connected to the wing forming a diamond shape in both top and plan view. This geometric arrangement utilizes the tail for both pitch control and as a structural support for the wing. Several researchers have studied this configuration and predicted significant reductions in trimmed drag or structural weight when compared with a conventional T-tail configuration. Kroo et al. compared the cruise drag of joined wings with conventional designs of the same lifting-surface area and structural weight. This study showed an 11 percent reduction in cruise drag for the lifting system of a joined wing. Although this reduction in cruise drag is significant, a complete design study is needed before any economic savings can be claimed for a joined-wing transport. Mission constraints, such as runway length, could increase the wing area and eliminate potential drag savings. Since other design codes do not accurately represent the interaction between structures and aerodynamics for joined wings, we developed a new design code for this study. The aerodynamic and structural analyses in this study are significantly more sophisticated than those used in most conventional design codes. This sophistication was needed to predict the aerodynamic interference between the wing and tail and the stresses in the truss-like structure. This paper describes these analysis methods, discusses some problems encountered when applying the numerical optimizer NPSOL, and compares optimum joined wings with conventional aircraft on the basis of cruise drag, lifting surface weight, and direct operating cost (DOC).
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center, The Third Air Force(NASA Symposium on Recent Advances in Multidisciplinary Analysis and Optimization; p 439-444
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The computation of induced drag with nonplanar and deformed wakes (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The classical calculation of inviscid drag, based on far field flow properties, is reexamined with particular attention to the nonlinear effects of wake roll-up. Based on a detailed look at nonlinear, inviscid flow theory, it is concluded that many of the classical, linear results are more general than might have been expected. Departures from the linear theory are identified and design implications are discussed. Results include the following: Wake deformation has little effect on the induced drag of a single element wing, but introduces first order corrections to the induced drag of a multi-element lifting system. Far field Trefftz-plane analysis may be used to estimate the induced drag of lifting systems, even when wake roll-up is considered, but numerical difficulties arise. The implications of several other approximations made in lifting line theory are evaluated by comparison with more refined analyses.
    Keywords: AERODYNAMICS
    Type: Stanford Univ., Nonlinear Aerodynanics and the Design of Wing Tips; 9 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Highly nonplanar lifting systems (1996)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: This paper deals with nonplanar wing concepts -- their advantages and possible applications in a variety of aircraft designs. A brief review and assessment of several concepts from winglets to ring wings is followed by a more detailed look at two recent ideas: exploiting nonplanar wakes to reduce induced drag, and applying a 'C-wing' design to large commercial transports. Results suggest that potential efficiency gains may be significant, while several nonaerodynamic characteristics are particularly interesting.
    Keywords: Aerodynamics
    Type: Transportation Beyond 2000: Technologies Needed for Engineering Design; 331-370; NASA-CP-10184-Pt-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Aircraft design optimization with multidisciplinary performance criteria (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The method described here for aircraft design optimization with dynamic response considerations provides an inexpensive means of integrating dynamics into aircraft preliminary design. By defining a dynamic performance index that can be added to a conventional objective function, a designer can investigate the trade-off between performance and handling (as measured by the vehicle's unforced response). The procedure is formulated to permit the use of control system gains as design variables, but does not require full-state feedback. The examples discussed here show how such an approach can lead to significant improvements in the design as compared with the more common sequential design of system and control law.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center, Recent Advances in Multidisciplinary Analysis and Optimization, Part 3; p 1219-1235
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Advanced Configurations for Very Large Subsonic Transport Airplanes (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent aerospace industry interest in developing a subsonic commercial transport airplane with 50 percent greater passenger capacity than the largest existing aircraft in this category (the Boeing 747-400 with approximately 400-450 seats) has generated a range of proposals based largely on the configuration paradigm established nearly 50 years ago with the Boeing B-47 bomber. While this basic configuration paradigm has come to dominate subsonic commercial airplane development since the advent of the Boeing 707/Douglas DC-8 in the mid-1950's, its extrapolation to the size required to carry more than 600-700 passengers raises several questions. To explore these and a number of related issues, a team of Boeing, university, and NASA engineers was formed under the auspices of the NASA Advanced Concepts Program. The results of a Research Analysis focused on a large, unconventional transport airplane configuration for which Boeing has applied for a patent are the subject of this report. It should be noted here that this study has been conducted independently of the Boeing New Large Airplane (NLA) program, and with the exception of some generic analysis tools which may be common to this effort and the NLA (as will be described later), no explicit Boeing NLA data other than that published in the open literature has been used in the conduct of the study reported here.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-CR-201614 , NAS 1.26:198351 , D6-81724
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Single-Winged Autorotating Brake for Sensor Deployment on Mars (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The following pages describe the development of a nonlinear simulation, results for the Martian entry problem, and a sizing study to determine whether the approach is feasible. The nonlinear simulation is described here and results are presented for several cases using Martian and Terrestrial atmosphere models. The results show that a 2.5 kg payload could be successfully delivered to the Martian surface using this approach and the report suggests an earth-based test of the system. Prior to the specific analysis presented here, a theoretical study of the mechanics of autorotation was completed, and a summary of this work is also included as part of this final report.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-CR-202165 , NAS 1.26:202165
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Simplified Aerodynamic and Structural Modeling for Oblique All-Wing Aircraft. Phase 2: Structures (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Any aircraft preliminary design study requires a structural model of the proposed configuration. The model must be capable of estimating the structural weight of a given configuration, and of predicting the deflections which will result from foreseen flight and ground loads. The present work develops such a model for the proposed Oblique All Wing airplane. The model is based on preliminary structural work done by Jack Williams and Peter Rudolph at Mdng, and is encoded in a FORTRAN program. As a stand-alone application, the program can calculate the weight CG location, and several types of structural deflections; used in conjunction with an aerodynamics model, the program can be used for mission analysis or sizing studies.
    Keywords: Aerodynamics
    Type: NASA-CR-202164 , NAS 1.26:202164
    Format: application/pdf
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