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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 289 records · Page 16
All sourcesNASA NTRSDOE OSTI
NASA NTRS1989

An efficient method for computing unsteady transonic aerodynamics of swept wings with control surfaces

A transonic equivalent strip (TES) method was further developed for unsteady flow computations of arbitrary wing planforms. The TES method consists of two consecutive correction steps to a given nonlinear code such as LTRAN2; namely, the chordwise mean flow correction and the spanwise phase correction. The computation procedure requires direct pressure input from other computed or measured data. Otherwise, it does not require airfoil shape or grid generation for given planforms. To validate the computed results, four swept wings of various aspect ratios, including those with control surfaces, are selected as computational examples. Overall trends in unsteady pressures are established with those obtained by XTRAN3S codes, Isogai's full potential code and measured data by NLR and RAE. In comparison with these methods, the TES has achieved considerable saving in computer time and reasonable accuracy which suggests immediate industrial applications.

Liu, D. D.↗
NASA NTRS1989

Some effects of aerodynamic spoilers on wing flutter

The effects of deployment angle and size of symmetrically mounted upper-surface and lower-surface spoilers on the flutter characteristics of a simple, paddle-like, low-aspect-ratio, rectangular wing model that was tested at Mach number 0.80 in the Langley Transonic Dynamics Tunnel are presented. The results show that the flutter dynamic pressure is increased by increasing either spoiler deployment angle or spoiler size. For the configurations studied spoiler size was more effective than deployment angle in increasing the flutter dynamic pressure.

Doggett, Robert V., Jr.↗