NACA-TR-1146

NASA - National Aeronautics and Space Administration (NASA)

Aerodynamic forces and loadings on symmetrical circular-arc airfoils with plain leading-edge and plain trailing-edge flaps

Organization:

NASA - National Aeronautics and Space Administration (NASA)

Year: 1953

Abstract: An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langley two-dimensional low-turbulence pressure tunnel of 6- and 10-percent-thick symmetrical circular-arc airfoil sections at low Mach numbers and several Reynolds numbers. The airfoils were equipped with 0.15-chord plain leading-edge saps and 0.20-chord plain trailing-edge flaps. The section lift and pitching-moment characteristics were determined for both airfoils with the flaps deflected individually and in combination, The section drag characteristics were obtained for the 6-percent-thick airfoil with the flaps partly deflected as low-drag-control flaps and for both airfoils with the flaps neutral. Surface pressures were measured on the 6-percent-thick airfoil section with the flaps deflected either individually or in appropriate combination to furnish flap load and hinge-moment data applicable to the structural design of the airfoil.
The experimental results showed maximum lift coefficients of 1.95 and 2.03 for the optimum combinations of deflection of leading-edge flaps and trailing-edge flaps as compared with 0.73 and 0.67 for the plain 6- and 10-percent-thick airfoils, respectively. Scale effect on the maximum lift coefficients was, in general, small. The aerodynamic center was ahead of the quarter-chord point and moved toward the leading edge when either the leading-edge flap or the trailing-edge flap was deflected. Deflecting the leading-edge flap was more effective in extending the low-drag range to higher section lift coefficients than deflecting the trailing-edge flap. The maximum flap normal-force and hinge-moment coefficients were, respectively, 4.74 and 2.24 for the leading-edge flap as compared with 1.48 and -0.61 for the trailing-edge flap.
A generalized method is developed that permits the determination of the chordwise pressure distribution over sharp-edge airfoils with plain leading-edge flaps and plain trailing-edge flaps of arbitrary size and deflection.

URI: https://yse.yabesh.ir/std/handle/yse/50635

Subject: AERODYNAMIC

Collections :

NASA - National Aeronautics and Space Administration (NASA)

Show full item record

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:47:45Z
date available	2017-09-04T15:47:45Z
date copyright	01/01/1953
date issued	1953
identifier other	PZDZYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/50635
description abstract	An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langley two-dimensional low-turbulence pressure tunnel of 6- and 10-percent-thick symmetrical circular-arc airfoil sections at low Mach numbers and several Reynolds numbers. The airfoils were equipped with 0.15-chord plain leading-edge saps and 0.20-chord plain trailing-edge flaps. The section lift and pitching-moment characteristics were determined for both airfoils with the flaps deflected individually and in combination, The section drag characteristics were obtained for the 6-percent-thick airfoil with the flaps partly deflected as low-drag-control flaps and for both airfoils with the flaps neutral. Surface pressures were measured on the 6-percent-thick airfoil section with the flaps deflected either individually or in appropriate combination to furnish flap load and hinge-moment data applicable to the structural design of the airfoil. The experimental results showed maximum lift coefficients of 1.95 and 2.03 for the optimum combinations of deflection of leading-edge flaps and trailing-edge flaps as compared with 0.73 and 0.67 for the plain 6- and 10-percent-thick airfoils, respectively. Scale effect on the maximum lift coefficients was, in general, small. The aerodynamic center was ahead of the quarter-chord point and moved toward the leading edge when either the leading-edge flap or the trailing-edge flap was deflected. Deflecting the leading-edge flap was more effective in extending the low-drag range to higher section lift coefficients than deflecting the trailing-edge flap. The maximum flap normal-force and hinge-moment coefficients were, respectively, 4.74 and 2.24 for the leading-edge flap as compared with 1.48 and -0.61 for the trailing-edge flap. A generalized method is developed that permits the determination of the chordwise pressure distribution over sharp-edge airfoils with plain leading-edge flaps and plain trailing-edge flaps of arbitrary size and deflection.
language	English
title	NACA-TR-1146	num
title	Aerodynamic forces and loadings on symmetrical circular-arc airfoils with plain leading-edge and plain trailing-edge flaps	en
type	standard
page	41
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1953
contenttype	fulltext
subject keywords	AERODYNAMIC
subject keywords	AIRCRAFT
subject keywords	AIRFOIL
subject keywords	AIRFOILS
subject keywords	BALANCE
subject keywords	BODIES
subject keywords	COEFFICIENTS
subject keywords	DEFLECTION
subject keywords	DISTRIBUTION
subject keywords	EDGES
subject keywords	EFFECT
subject keywords	FORCES
subject keywords	LEADING
subject keywords	LIFT
subject keywords	LOADS
subject keywords	PARTS
subject keywords	PRESSURE
subject keywords	PROFILES
subject keywords	SCALE
subject keywords	SYMMETRICAL
subject keywords	TESTS
subject keywords	TORQUE
subject keywords	TRAILING
subject keywords	TUNNEL
subject keywords	WIND