Optimization of the double-slot blown airfoil with jet at the leading and trailing edges of the flap
AIP AdvancesAn active lift augmentation technique combining trailing edge blowing and blown flap is explored in this study. A double-slot blown flap airfoil is designed based on NACA23015.
Songlin Xiang +3 more
doaj +1 more source
Experimental study of the effect on span loading on aircraft wakes [PDF]
Measurements were made in the NASA-Ames 40- by 80-foot wind tunnel of the rolling moment induced on a following model in the wake 13.6 spans behind a subsonic transport model for a variety of trailing edge flap settings of the generator.
Ciffone, D. L. +2 more
core +1 more source
Investigation of jet-installation noise sources under static conditions [PDF]
The acoustical effects of operating a 6-cm exit-diameter nozzle in the presence of a wing-flap model under static conditions are examined experimentally.
Shearin, J. G.
core +1 more source
Distributed upper-surface blowing concept [PDF]
A low speed investigation was conducted in the Langley V/STOL tunnel to determine the powered lift aerodynamic performance of a distributed upper surface blown propulsive lift transport model.
Coe, P. L., Jr., Fournier, P. G.
core +1 more source
Applied SciencesFollowing the promising performance of the seamless morphing trailing edge (SMTE) flap and its internal actuation system, the elephant trunk mechanism (ETM), investigated through aerodynamic and structural analyses, this study presents an experimental ...
Mir Hossein Negahban +2 more
doaj +1 more source
Validation of a pair of computer codes for estimation and optimization of subsonic aerodynamic performance of simple hinged-flap systems for thin swept wings [PDF]
Extensive correlations of computer code results with experimental data are employed to illustrate the use of linearized theory attached flow methods for the estimation and optimization of the aerodynamic performance of simple hinged flap systems.
Carlson, Harry W., Darden, Christine M.
core +1 more source
The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear [PDF]
Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges.
Harris, Thomas E, Weick, Fred E
core +1 more source
Interim noise correlation for some OTW configurations using external jet-flow deflectors [PDF]
Jet flap interaction acoustic data obtained statically from a model-scale study of STOL-OTW configurations with a conical nozzle mounted above the wing and using various external deflectors to provide jet-flow attachment are correlated. The acoustic data
Groesbeck, D. E., Vonglahn, U. H.
core +1 more source
Low-speed wind-tunnel investigation of a large scale advanced arrow-wing supersonic transport configuration with engines mounted above wing for upper-surface blowing [PDF]
Tests have been conducted in a full scale tunnel to determine the low speed aerodynamic characteristics of a large scale advanced arrow wing supersonic transport configuration with engines mounted above the wing for upper surface blowing. Tests were made
Coe, P. L., Jr. +2 more
core +1 more source
Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls [PDF]
, 1958 An investigation has been made to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and with all-movable control surfaces.
Bernot, P. T., Robinson, R. B.
core +2 more sources