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Performance, Stability, and Control Investigation at Mach Numbers from 0.4 to 0.9 of a Model of the "Swallow" with Outer Wing Panels Swept 25 degree with and without Power SimulationAn investigation of the performance, stability, and control characteristics of a variable-sweep arrow-wing model (the "Swallow") with the outer wing panels swept 25 deg has been conducted in the Langley 16-foot transonic tunnel. The wing was uncambered and untwisted and had RAE 102 airfoil sections with a thickness-to-chord ratio of 0.14 normal to the leading edge. Four outboard engines located above and below the wing provided propulsive thrust, and, by deflecting in the pitch direction and rotating in the lateral plane, also produced control forces. A pair of swept lateral fins and a single vertical fin were mounted on each engine nacelle to provide aerodynamic stability and control. Jets-off data were obtained with flow-through nacelles, stimulating the effects of inlet flow; jet thrust and hot-jet interference effects were obtained with faired-nose nacelles housing hydrogen peroxide gas generators. Six-component force and moment data were obtained through a Mach number range of 0.40 to 0.90 at angles of attack and angles of sideslip from 0 deg to 15 deg. Longitudinal, directional, and lateral control were obtained by deflecting the nacelle-fin combinations as elevators, rudders, and ailerons at several fixed angles for each control.
Document ID
19980228396
Acquisition Source
Headquarters
Document Type
Technical Memorandum (TM)
Authors
Runckel, Jack F. (NASA Langley Research Center Hampton, VA United States)
Schmeer, James W. (NASA Langley Research Center Hampton, VA United States)
Cassetti, Marlowe D. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
May 3, 1960
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TM-SX-296
L-975
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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