17,003 Documents in our Technical Library
1344576 Total Downloads

Newest Additions

ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...
MIL-R-7885D General Specification for Rivets, Blind, Structural, Mechanically Locked Spindle and Friction Locked Spindle
This specification covers mechanically locked spindle and  friction locked spindle ...
MIL-HDBK-132A Protective Finishes for Metal and Wood Surfaces
The primary object of this handbook is to provide a ...

naca-wr-a-11

  • Version
  • 30 Downloads
  • 1.76 MB File Size
  • 1 File Count
  • April 15, 2017 Create Date
  • April 15, 2017 Last Updated
Scroll for Details

Computation of Hinge Moment Characteristics of Horizontal Tails from Section Data

A study of data from various wind—tunnel tests of hori—
zontal tail surfaces was made to determine the accuracy with
which section data can be used to estimate the hinge—moment
characteristics of control surfaces of finite span. The study
consisted of a comparison between the variation of elevator
hinge moments with elevator deflection and with airplane pitch—
ing moment, as estimated from data obtained in two—dimensional
flow, and that variation measured emperimentally on 16 differ—
ent horizontal tails mounted on wind—tunnel models of complete
airplanes. The method used in applying section data to the
evaluation of three—dimensional characteristics is outlined,
and summary curves showing the variation of the major param—
eters with control—surface chord, balance chord, and trailing—
edge angle are presented. It is demonstrated that the three—
dimensional hinge—moment characteristics of tail surfaces can
be derived from existing section data with an accuracy which
is within the tolerance required in preliminary design,

Considerable data on the characteristics of large—chord
flaps have been obtained (references 1 to 11), which establish
the effect of the major variables (flap chord, balance chord,
nose shape, nose gap, etc‘) on the section aerodynamic charac—
teristics of airfoils. The question has arisen on occasion,
as to the degree of accuracy with which these data can be
applied to the estimation of the characteristics of control
surfaces in threeadimensional flow. This question is partic—
ularly pertinent as applied to the horizontal or vertical
tail surfaces of complete airplanes, since these surfaces
(as distinguished from ailerons) are subjected to mutual
interferences, fuselage interference, and are of relatively
low aspect ratio, so that the differences caused by these
“secondary" effects might be so large as to preclude the
use of section data for anything but the most approximate
detimates.

In order to shed some light on this problem, the en—
pcrimentally measured hinge~moment and pitching—moment chan-
acteristics of 16 different horizontal tail surfaces mounted
on Complete airplane models have been compiled and are com—
pared with characteristics estimated from data obtained in
two~dimensional flow. This study has taken the form of the
comparison of hinge—moment characteristics as defined by
the variation of elevator hinge moments with elevator angle,
with tail angle of attack, and with airplane pitching moments.
The types of aerodynamic belancn‘ocnsidered in the present
investigation include internally scaled nose balance and un—
shrouded nose overhang balance.

Comment On This Post

Your email address will not be published. Required fields are marked *

FileAction
naca-wr-a-11 Computation of Hinge Moment Characteristics of Horizontal Tails from Section Data.pdfDownload 

naca-wr-a-11

  • Version
  • 30 Downloads
  • 1.76 MB File Size
  • 1 File Count
  • April 15, 2017 Create Date
  • April 15, 2017 Last Updated
Scroll for Details

Computation of Hinge Moment Characteristics of Horizontal Tails from Section Data

A study of data from various wind—tunnel tests of hori—
zontal tail surfaces was made to determine the accuracy with
which section data can be used to estimate the hinge—moment
characteristics of control surfaces of finite span. The study
consisted of a comparison between the variation of elevator
hinge moments with elevator deflection and with airplane pitch—
ing moment, as estimated from data obtained in two—dimensional
flow, and that variation measured emperimentally on 16 differ—
ent horizontal tails mounted on wind—tunnel models of complete
airplanes. The method used in applying section data to the
evaluation of three—dimensional characteristics is outlined,
and summary curves showing the variation of the major param—
eters with control—surface chord, balance chord, and trailing—
edge angle are presented. It is demonstrated that the three—
dimensional hinge—moment characteristics of tail surfaces can
be derived from existing section data with an accuracy which
is within the tolerance required in preliminary design,

Considerable data on the characteristics of large—chord
flaps have been obtained (references 1 to 11), which establish
the effect of the major variables (flap chord, balance chord,
nose shape, nose gap, etc‘) on the section aerodynamic charac—
teristics of airfoils. The question has arisen on occasion,
as to the degree of accuracy with which these data can be
applied to the estimation of the characteristics of control
surfaces in threeadimensional flow. This question is partic—
ularly pertinent as applied to the horizontal or vertical
tail surfaces of complete airplanes, since these surfaces
(as distinguished from ailerons) are subjected to mutual
interferences, fuselage interference, and are of relatively
low aspect ratio, so that the differences caused by these
“secondary" effects might be so large as to preclude the
use of section data for anything but the most approximate
detimates.

In order to shed some light on this problem, the en—
pcrimentally measured hinge~moment and pitching—moment chan-
acteristics of 16 different horizontal tail surfaces mounted
on Complete airplane models have been compiled and are com—
pared with characteristics estimated from data obtained in
two~dimensional flow. This study has taken the form of the
comparison of hinge—moment characteristics as defined by
the variation of elevator hinge moments with elevator angle,
with tail angle of attack, and with airplane pitching moments.
The types of aerodynamic belancn‘ocnsidered in the present
investigation include internally scaled nose balance and un—
shrouded nose overhang balance.

FileAction
naca-wr-a-11 Computation of Hinge Moment Characteristics of Horizontal Tails from Section Data.pdfDownload 
17,003 Documents in our Technical Library
1344576 Total Downloads

Search The Technical Library

Newest Additions

ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...
MIL-R-7885D General Specification for Rivets, Blind, Structural, Mechanically Locked Spindle and Friction Locked Spindle
This specification covers mechanically locked spindle and  friction locked spindle ...
MIL-HDBK-132A Protective Finishes for Metal and Wood Surfaces
The primary object of this handbook is to provide a ...