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  • 1
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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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  • 2
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    Subsonic longitudinal and lateral-directional characteristics of a forward-swept-wing fighter configuration at angles of attack up to 47 deg (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Subsonic lateral-direction and longitudinal characteristics of a forward-swept-wing fighter configuration were examined in wind-tunnel tests at Mach numbers of 0.2 and 0.5 for angles of attack from -7 to 47 deg. and over a sidelslip range of +/- 15 deg. The effects of a canard, strakes, vertical tail, and leading- and trailing-edge flaps are examined. The canard and strakes both reduce asymmetric moments and side forces at zero sideslip for angles of attack up to about 30 deg. The canard has a small influence on lateral-directional stability; however, strakes produce a substantial reduction in lateral stability for angles of attack greater than about 20 deg. The vertical tail improves directional stability for angles of attack up to 30 deg. Deflection of the leading-edge flap to 20 deg. at high angles of attack on the strake and canard configurations degrades lateral and directional stability. Deflection of the trailing-edge flap to 20 deg. on the canard configuration generally increases lateral and directional stability at high angles of attack. Leading- and trailing-edge flaps on the wing-body and canard configurations are effective for increased lift only for angles of attack up to about 40 deg. The leading-edge flap remains effective on the strake configuration over the entire angle-of-attack range tested.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2727 , L-16206 , NAS 1.60:2727
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  • 3
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    Forward-swept wing configuration designed for high maneuverability by use of a transonic computational method (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A transonic computational analysis method and a transonic design procedure have been used to design the wing and the canard of a forward-swept-wing fighter configuration for good transonic maneuver performance. A model of this configuration was tested in the Langley 16-Foot Transonic Tunnel. Oil-flow photographs were obtained to examine the wind flow patterns at Mach numbers from 0.60 to 0.90. The transonic theory gave a reasonably good estimate of the wing pressure distributions at transonic maneuver conditions. Comparison of the forward-swept-wing configuration with an equivalent aft-swept-wing-configuration showed that, at a Mach number of 0.90 and a lift coefficient of 0.9, the two configurations have the same trimmed drag. The forward-swept wing configuration was also found to have trimmed drag levels at transonic maneuver conditions which are comparable to those of the HiMAT (highly maneuverable aircraft technology) configuration and the X-29 forward-swept-wing research configuration. The configuration of this study was also tested with a forebody strake.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2628 , L-16120 , NAS 1.60:2628
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  • 4
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    An assessment of current methods for drag-due-to-lift minimization at supersonic speeds (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The estimation and minimization of drag-due-to-lift at supersonic speeds has been examined in this study. Correlations of theory with experimental data are used to assess the applicability and limitations of the linearized theory. The role of leading-edge thrust and the use of twist and camber to develop distributed thrust are also discussed. A semiempirical design and estimation method which takes into account the shortcomings of the linear theory is presented. The use of this method will allow the design of more nearly optimum lifting surfaces and provide an accurate prediction of their level of performance. A preliminary examination is made of the use of an Euler code for estimation of the aerodynamic characteristics of a twisted and cambered wing.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3302
    Format: text
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  • 5
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    Aerodynamic design for improved manueverability by use of three-dimensional transonic theory (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Improvements in transonic maneuver performance by the use of three-dimensional transonic theory and a transonic design procedure were examined. The FLO-27 code of Jameson and Caughey was used to design a new wing for a fighter configuration with lower drag at transonic maneuver conditions. The wing airfoil sections were altered to reduce the upper-surface shock strength by means of a design procedure which is based on the iterative application of the FLO-27 code. The plan form of the fighter configuration was fixed and had a leading edge sweep of 45 deg and an aspect ratio of 3.28. Wind-tunnel tests were conducted on this configuration at Mach numbers from 0.60 to 0.95 and angles of attack from -2 deg to 17 deg. The transonic maneuver performance of this configuration was evaluated by comparison with a wing designed by empirical methods and a wing designed primarily by two-dimensional transonic theory. The configuration designed by the use of FLO-27 had the same or lower drag than the empirical wing and, for some conditions, lower drag than the two-dimensional design. From some maneuver conditions, the drag of the two-dimensional design was somewhat lower.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2282 , L-15681 , NAS 1.60:2282
    Format: application/pdf
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  • 6
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    Low-speed investigation of effects of wing leading- and trailing-edge flap deflections and canard incidence on a fighter configuration equipped with a forward-swept wing (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An advanced fighter configuration with a forward-swept wing of aspect ratio 3.28 is tested in the Langley 7 by 10 Foot High Speed Tunnel at a Mach number of 0.3. The wing has 29.5 degrees of forward sweep of the quarter chord line and is equipped with 15 percent chord leading edge and 30 percent chord trailing edge flaps. The canard is sweptback 45 degrees. Tests were made through a range of angle of attack from about -2 degrees to 22 degrees. Deflecting the flaps significantly improves the lift drag characteristics at the higher angles of attack. The canard is able to trim the configurations with different flap deflections over most of the range of angle of attack. The penalty in maximum lift coefficient due to trimming is about 0.10.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85795 , L-15746 , NAS 1.15:85795
    Format: application/pdf
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  • 7
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    Wind-tunnel/flight correlation study of aerodynamic characteristics of a large flexible supersonic cruise airplane (XB-701) 2: Extrapolation of wind-tunnel data to full-scale conditions (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of calculations necessary to extrapolate performance data on an XB-70-1 wind tunnel model to full scale at Mach numbers from 0.76 to 2.53 are presented. The extrapolation was part of a joint program to evaluate performance prediction techniques for large flexible supersonic airplanes similar to a supersonic transport. The extrapolation procedure included: interpolation of the wind tunnel data at the specific conditions of the flight test points; determination of the drag increments to be applied to the wind tunnel data, such as spillage drag, boundary layer trip drag, and skin friction increments; and estimates of the drag items not represented on the wind tunnel model, such as bypass doors, roughness, protuberances, and leakage drag. In addition, estimates of the effects of flexibility of the airplane were determined.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1515 , L-12688
    Format: application/pdf
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  • 8
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    Supercritical maneuvering fighter configuration. Wind-tunnel investigation at Mach numbers of 0.60 to 0.95 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation was conducted to study the application of supercritical technology to highly maneuverable combat aircraft. The configuration studied has a leading-edge sweep of 45 deg and an aspect ratio of 3.28. Two supercritical-wing shapes were tested at Mach numbers from 0.60 to 0.95 with angles of attack from -2 deg to 17 deg. On supercritical wing was designed to achieve a high level of transonic maneuver performance at a Mach number of 0.90; however, excessive flow separation developed on this wing at a Mach number of 0.85. A second supercritical wing was tested which had significantly reduced flow separation and improved drag characteristics at a Mach number of 0.85 and maintained the performance of the original wing at the higher Mach numbers. Leading-edge vortex generators did not improve the performance of the second wing; however, a sharp leading-edge flap produced sizable drag reductions at Mach numbers from 0.60 to 0.90.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84513 , L-15399 , NAS 1.15:84513
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  • 9
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    Low-speed upwash interference on a transport model in a rectangular slotted-wall wind tunnel (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was made of the upwash interference caused by the wind tunnel walls at a Mach number of 0.20. The wind tunnel has slotted horizontal walls and solid vertical walls and the wind tunnel model is a wing-fuselage combination typical of a short take-off and landing (STOL) transport. Measurements were made of the model forces and angle of attack. The experimental results are compared to theoretical solutions for the upwash interference. This comparison enabled an indirect determination of one of the constants in the slotted wall boundary condition. The magnitude of the experimental upwash interference is also compared to the accuracy of the data. This comparison indicates that it is difficult to make definite conclusions based on the experimental data. Suggestions are made for future research which could provide a practical means of accurately determining the wall-interference velocities in wind tunnels with rigid slotted walls.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3218 , L-10042
    Format: application/pdf
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  • 10
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    Subsonic annular wing theory with application to flow about nacelles (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method has recently been developed for calculating the flow over a subsonic nacelle at zero angle of attack. The method makes use of annular wing theory and boundary-layer theory and has shown good agreement with both experimental data and more complex theoretical solutions. The method permits variation of the mass flow by changing the size of a center body.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7630 , L-9274
    Format: application/pdf
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