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  • 1
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    Prediction of Airplane Sonic-Boom Pressure Fields (1965)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: This paper presents a discussion of the sensitivity of supersonic-transport design and operation to sonic-boom considerations and shows the necessity for a study of these problems early in the development program. Methods of predicting pressure signatures are outlined and examples of the correlation of these estimates with wind-tunnel and flight measurements are shown. Estimates of sonic-boom characteristics for a representative supersonic transport show that in the critical transonic acceleration portion of the flight, overpressures somewhat lower than estimated by the use of far-field assumptions may be expected. Promising design possibilities for the achievement of further overpressure reductions are explored.
    Keywords: Acoustics
    Type: NASA Conference on Aircraft Operating Problems: A Compilation of the Papers Presented; 235-244
    Format: text
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  • 2
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    Improved Method for Prediction of Attainable Wing Leading-Edge Thrust (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Prediction of the loss of wing leading-edge thrust and the accompanying increase in drag due to lift, when flow is not completely attached, presents a difficult but commonly encountered problem. A method (called the previous method) for the prediction of attainable leading-edge thrust and the resultant effect on airplane aerodynamic performance has been in use for more than a decade. Recently, the method has been revised to enhance its applicability to current airplane design and evaluation problems. The improved method (called the present method) provides for a greater range of airfoil shapes from very sharp to very blunt leading edges. It is also based on a wider range of Reynolds numbers than was available for the previous method. The present method, when employed in computer codes for aerodynamic analysis, generally results in improved correlation with experimental wing-body axial-force data and provides reasonable estimates of the measured drag.
    Keywords: Aerodynamics
    Type: NASA-TP-3557 , L-17440 , NAS 1.60:3557
    Format: application/pdf
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  • 3
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    Guide to AERO2S and WINGDES Computer Codes for Prediction and Minimization of Drag Due to Lift (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The computer codes, AER02S and WINGDES, are now widely used for the analysis and design of airplane lifting surfaces under conditions that tend to induce flow separation. These codes have undergone continued development to provide additional capabilities since the introduction of the original versions over a decade ago. This code development has been reported in a variety of publications (NASA technical papers, NASA contractor reports, and society journals). Some modifications have not been publicized at all. Users of these codes have suggested the desirability of combining in a single document the descriptions of the code development, an outline of the features of each code, and suggestions for effective code usage. This report is intended to supply that need.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TP-3637 , NAS 1.60:3637 , L-17546
    Format: application/pdf
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  • 4
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    Survey and analysis of research on supersonic drag-due-to-lift minimization with recommendations for wing design (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A survey of research on drag-due-to-lift minimization at supersonic speeds, including a study of the effectiveness of current design and analysis methods was conducted. The results show that a linearized theory analysis with estimated attainable thrust and vortex force effects can predict with reasonable accuracy the lifting efficiency of flat wings. Significantly better wing performance can be achieved through the use of twist and camber. Although linearized theory methods tend to overestimate the amount of twist and camber required for a given application and provide an overly optimistic performance prediction, these deficiencies can be overcome by implementation of recently developed empirical corrections. Numerous examples of the correlation of experiment and theory are presented to demonstrate the applicability and limitations of linearized theory methods with and without empirical corrections. The use of an Euler code for the estimation of aerodynamic characteristics of a twisted and cambered wing and its application to design by iteration are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3202 , L-16963 , NAS 1.60:3202
    Format: application/pdf
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  • 5
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    The design and analysis of simple low speed flap systems with the aid of linearized theory computer programs (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose here is to show how two linearized theory computer programs in combination may be used for the design of low speed wing flap systems capable of high levels of aerodynamic efficiency. A fundamental premise of the study is that high levels of aerodynamic performance for flap systems can be achieved only if the flow about the wing remains predominantly attached. Based on this premise, a wing design program is used to provide idealized attached flow camber surfaces from which candidate flap systems may be derived, and, in a following step, a wing evaluation program is used to provide estimates of the aerodynamic performance of the candidate systems. Design strategies and techniques that may be employed are illustrated through a series of examples. Applicability of the numerical methods to the analysis of a representative flap system (although not a system designed by the process described here) is demonstrated in a comparison with experimental data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3913 , NAS 1.26:3913
    Format: application/pdf
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  • 6
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    An Investigation of Some Aspects of the Sonic Boom by Means of Wind-Tunnel Measurements of Pressures About Several Bodies at a Mach Number of 2.01 (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of some aspects of the sonic boom has been made with the aid of wind-tunnel measurements of the pressure distributions about bodies of various shapes. The tests were made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and at a Reynolds number per foot of 2.5 x 10(exp 6). Measurements of the pressure field were made at orifices in the surface of a boundary-layer bypass plate. The models which represented both fuselage and wing types of thickness distributions were small enough to allow measurements as far away as 8 body lengths or 64 chords. The results are compared with estimates made using existing theory. To the first order, the boom-producing pressure rise across the bow shock is dependent on the longitudinal development of body area and not on local details. Nonaxisymmetrical shapes may be replaced by equivalent bodies of revolution to obtain satisfactory theoretical estimates of the far-field pressures.
    Keywords: Aerodynamics
    Type: NASA-TN-D-161
    Format: application/pdf
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  • 7
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    Applicability of linearized-theory attached-flow methods to design and analysis of flap systems at low speeds for thin swept wings with sharp leading edges (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Low-speed experimental force and data on a series of thin swept wings with sharp leading edges and leading and trailing-edge flaps are compared with predictions made using a linearized-theory method which includes estimates of vortex forces. These comparisons were made to assess the effectiveness of linearized-theory methods for use in the design and analysis of flap systems in subsonic flow. Results demonstrate that linearized-theory, attached-flow methods (with approximate representation of vortex forces) can form the basis of a rational system for flap design and analysis. Even attached-flow methods that do not take vortex forces into account can be used for the selection of optimized flap-system geometry, but design-point performance levels tend to be underestimated unless vortex forces are included. Illustrative examples of the use of these methods in the design of efficient low-speed flap systems are included.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2653 , L-16151 , NAS 1.60:2653
    Format: application/pdf
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  • 8
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    A Pressure-distribution Investigation of the Aerodynamic Characteristics of a Body of Revolution in the Vicinity of a Reflection Plane at Mach Numbers of 1.41 and 2.01 (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The changes in the aerodynamic characteristics of a body of revolution with a fineness ratio of 8 have been determined at Mach numbers of 1.41 and 2.01, a Reynolds number, based on body length, of 4.54 x 10 to the 6th power, and angles of incidence of 0 degrees and plus or minus 3 degrees as the position of the body is varied with respect to a reflection plane. The data are compared with theoretical results.
    Type: NACA-RM-L54J29
    Format: application/pdf
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  • 9
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    The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations II : swept-wing-heavy-bomber configuration with large store (nacelle). lateral forces and pitching moment (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-L55E26a
    Format: application/pdf
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  • 10
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    Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-L57J23
    Format: application/pdf
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