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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 343 records · Page 19
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Longitudinal aerodynamic characteristics of a large scale model with a swept wing and augmented jet flap in ground effect

The investigation of the in-ground-effect, longitudinal aerodynamic characteristics of a large scale swept augmentor wing model is presented, using 40 x 80 ft wind tunnel. The investigation was conducted at three ground heights; h/c equals 2.01, 1.61, and 1.34. The induced effect of underwing nacelles, was studied with two powered nacelle configurations. One configuration used four JT-15D turbofans while the other used two J-85 turbojet engines. Two conical nozzles on each J-85 were used to deflect the thrust at angles from 0 to 120 deg. Tests were also performed without nacelles to allow comparison with previous data from ground effect.

Falarski, M. D.↗
NASA NTRS1995

A parametric study of supersonic laminar flow for swept wings using linear stability analysis

A parametric study to predict the extent of laminar flow on the upper surface of a generic swept-back wing (NACA 64A010 airfoil section) at supersonic speeds was conducted. The results were obtained by using surface pressure predictions from an Euler/Navier-Stokes computational fluid dynamics code coupled with a boundary layer code, which predicts detailed boundary layer profiles, and finally with a linear stability code to determine the extent of laminar flow. The parameters addressed are Reynolds number, angle of attack, and leading-edge wing sweep. The results of this study show that an increase in angle of attack, for specific Reynolds numbers, can actually delay transition. Therefore, higher lift capability, caused by the increased angle of attack, as well as a reduction in viscous drag due to the delay in transition is possible for certain flight conditions.

Cummings, Russell M.↗
NASA NTRS1973

Effects of wing height on low-speed aerodynamic characteristics of a model having a 42 deg swept wing, a supercritical airfoil, double-slotted flaps, and a low tail

A low speed investigation was conducted in the Langley V/STOL tunnel to determine the static longitudinal lateral stability characteristics of a general research model with the wing in a high position and a low position on the fuselage. The model had a wing with a quarter chord sweep of 42 deg, an aspect ratio of 6.78, a supercritical airfoil, and a high lift system which consisted of a leading edge slat and a double slotted flap. Various slat and flap deflections represented clean, take off, and landing configurations. A 45 deg swept horizontal tail located slightly below the fuselage center line was investigated with both the low and high wing configurations.

Fournier, P. G.↗
NASA NTRS1978

Wind tunnel tests on a tail-less swept wing span-distributed cargo aircraft configuration

The configuration consisted of a 30 deg -swept, untapered, untwisted wing utilizing a low-moment cambered airfoil of 20 percent streamwise thickness designed for low wave drag at M = 0.6, C sub L = 0.4. The tests covered a range of Mach numbers 0.3 to 0.725 and chord Reynolds number 1,100,000 to 2,040,000, angles of attack up to model buffet and sideslip angles + or - 4 deg. Configuration build up, wing pod filleting, airfoil modification and trailing edge control deflection effects were briefly investigated. Three wing tip vertical tail designs were also tested. Wing body filleting and a simple airfoil modification both produced increments to maximum lift/drag ratio. Addition of pods eliminated pitch instability of the basic wing. While the magnitude of these benefits probably was Reynolds number sensitive, they underline the potential for improving the aerodynamics of the present configuration. The cruise parameter (product of Mach number and lift/drag ratio) attained a maximum close to the airfoil design point. The configuration was found to be positively stable with normal control effectiveness about all three axes in the Mach number and C sub L range of interest.

Rao, D. M.↗
NASA NTRS1972

Numerical calculation of transonic flow about swept wings.

Description of a mixed elliptic-hyperbolic relaxation algorithm which calculates solutions to the three-dimensional, nonlinear transonic small disturbance potential equation for flows about thin swept lifting wings with free-stream Mach number less than 1. The algorithm is designed to treat supercritical flows, including cases with embedded shock waves. Nonrectangular planform shapes, including sweep and taper, are treated by a coordinate transformation which maps the wing planform into a rectangle. Computed results at angles of attack of 0 and 2 deg for a AR = 4, constant chord, 23.75 deg sweptback planform model with a Lockheed C141 airfoil section are compared with data obtained experimentally for both subcritical and supercritical flows. Subcritical results are also compared with those obtained by a subsonic 'panel' method.

Ballhaus, W. F.↗
NASA NTRS1988

Design aspects of long range supersonic LFC airplanes with highly swept wings

The achievement of natural LFC in SST configurations featuring externally braced, very highly swept, high structural aspect ratio wing planforms results in outstandingly high cruise L/D ratios while maintaining low sonic-boom overpressures. A conceptual design study has been conducted with a view to range capability maximization in SSTs. A three-body configuration employing a highly swept, strut-braced planform, in which a central fuselage and two smaller outboard bodies alleviate structural wing bending and torsion, is noted to allow further increases in wingspan and aspect ratio which commensurately reduce lift-induced wave-plus-vortex drag and volume-induced wave drag.

Pfenninger, Werner↗
NASA NTRS1990

Parametric analysis of swept-wing geometry with sheared wing tips

A computational parameter study is presented of potential reductions in induced drag and increases in lateral-directional stability due to sheared wing tips attached to an untwisted wing of moderate sweep and aspect ratio. Sheared tips are swept and tapered wing-tip devices mounted in the plane of the wing. The induced-drag results are obtained using an inviscid, incompressible surface-panel method that models the nonlinear effects due to the deflected and rolled-up wake behind the lifting surface. The induced-drag results with planar sheared tips are compared to straight-tapered tip extensions and nonplanar winglet geometries. The lateral-directional static-stability characteristics of the wing with sheared tips are estimated using a quasi-vortex-lattice method. For certain combinations of sheared-tip sweep and taper, both the induced efficiency of the wing and the relevant static-stability derivatives are predicted to increase compared to the wing with a straight-tapered tip modification.

Fremaux, C. M.↗
NASA NTRS1985

The buffeting pressure field of a high-aspect-ratio swept wing

An experimental study of the fluctuating pressure field of a high-aspect-ratio swept transport-type wing model in transonic buffeting flow is examined. A high degree of similarity between the buffet-related features of the wing flowfield and 2-D transonic flowfields is indicated. At several spanwise stations, unsteady lift produced by the pressure fluctuations is evaluated and found to increase in intensity as local flow separation develops. Results show that although the wing does vibrate, the measured lift fluctuations are driving, and not driven by wing vibrations. The influence of tunnel-flow unsteadiness on the data is considered.

Roos, F. W.↗
NASA NTRSDate not supplied

Comparison of Ice Shapes on Full-Chord and Truncated Swept Wing Models

A research program was conducted to evaluate the effectiveness of icing tunnel hybrid model design. A hybrid design is where the full-scale leading edge of a wing section is maintained only to a certain percentage of the local chord, while the aft section of the model is redesigned into a shortened or truncated planform. Ice shape geometries on a full-chord length and hybrid versions of the swept CRM65 wing model were obtained in NASA Icing Research Tunnel and compared. For most test conditions, the overall size and shape of the ice shapes compared well. On the main part of the ice shape, the hybrid model had larger chordwise extent, resulting in wider ice shape. For the scallop ice shapes, the ice shape heights at attachment line location were identical. For conditions that produced rime shape, hybrid model ice shapes were larger overall, even at the attachment line location. The only location where there was more ice on the full chord model was on the lower surface, downstream of where the hybrid model no longer had full-scale leading edge. For the test conditions where ice mass measurements were acquired for both models, the full-chord models had 11-22% less ice mass than on the hybrid wing. These differences were larger and opposite of those predicted from LEWICE 3D ice prediction calculations. Further investigation is needed in order determine the cause of the differences between the full-chord and hybrid models.

Icing↗
NASA NTRSDate not supplied

Comparison of Ice Shapes on Full-Chord and Truncated Swept Wing Models

A research program was conducted to evaluate the effectiveness of icing tunnel hybrid model design. A hybrid design is where the full-scale leading edge of a wing section is maintained only to a certain percentage of the local chord, while the aft section of the model is redesigned into a shortened or truncated planform. Ice shape geometries on a full-chord length and hybrid versions of the swept CRM65 wing model were obtained in NASA Icing Research Tunnel and compared. For most test conditions, the overall size and shape of the ice shapes compared well. On the main part of the ice shape, the hybrid model had larger chordwise extent, resulting in wider ice shape. For the scallop ice shapes, the ice shape heights at attachment line location were identical. For conditions that produced rime shape, hybrid model ice shapes were larger overall, even at the attachment line location. The only location where there was more ice on the full chord model was on the lower surface, downstream of where the hybrid model no longer had full-scale leading edge. For the test conditions where ice mass measurements were acquired for both models, the full-chord models had 11-22% less ice mass than on the hybrid wing. These differences were larger and opposite of those predicted from LEWICE 3D ice prediction calculations. Further investigation is needed in order determine the cause of the differences between the full-chord and hybrid models.

Icing↗