Control-surface hinge-moment calculations for a high-aspect-ratio supercritical wing
The hinge moments, at selected flight conditions, resulting from deflecting two trailing edge control surfaces (one inboard and one midspan) on a high aspect ratio, swept, fuel conservative wing with a supercritical airfoil are estimated. Hinge moment results obtained from procedures which employ a recently developed transonic analysis are given. In this procedure a three dimensional inviscid transonic aerodynamics computer program is combined with a two dimensional turbulent boundary layer program in order to obtain an interacted solution. These results indicate that trends of the estimated hinge moment as a function of deflection angle are similar to those from experimental hinge moment measurements made on wind tunnel models with swept supercritical wings tested at similar values of free stream Mach number and angle of attack.
- Research Organization:
- National Aeronautics and Space Administration, Langley AFB, VA (USA). Langley Research Center
- OSTI ID:
- 6144273
- Report Number(s):
- N-78-31043
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
AIRCRAFT
FUEL CONSUMPTION
AIRFOILS
AERODYNAMICS
AIRCRAFT COMPONENTS
BOUNDARY LAYERS
COMPUTER CODES
CONTROL
MACH NUMBER
NUMERICAL SOLUTION
TURBULENT FLOW
WIND TUNNELS
ENERGY CONSUMPTION
FLUID FLOW
FLUID MECHANICS
LAYERS
MECHANICS
TUNNELS
VELOCITY
320201* - Energy Conservation
Consumption
& Utilization- Transportation- Air & Aerospace