Research abstracts

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Material Information

Title:
Research abstracts
Physical Description:
93 v. : ; 27 cm.
Language:
English
Creator:
United States -- National Advisory Committee for Aeronautics
Publisher:
National Advisory Committee for Aeronautics
Place of Publication:
Washington, D.C
Publication Date:
Frequency:
irregular
completely irregular

Subjects

Subjects / Keywords:
Aeronautics -- Abstracts -- Periodicals   ( lcsh )
Aeronautics -- Research -- Abstracts -- Periodicals   ( lcsh )
Genre:
serial   ( sobekcm )
federal government publication   ( marcgt )
abstract or summary   ( marcgt )

Notes

Statement of Responsibility:
National Advisory Committee for Aeronautics.
Dates or Sequential Designation:
Abstracts no. 1 (June 15, 1951)-no. 93 (Nov. 30, 1955).

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 001469326
notis - AGY1019
oclc - 01471285
lccn - 86657025
issn - 0499-9274
Classification:
lcc - TL501 .U5895
System ID:
AA00009235:00085

Related Items

Preceded by:
Monthly list of documents released by the NACA ...
Succeeded by:
Research abstracts and reclassification notice


This item is only available as the following downloads:


Full Text





National


S.
a


SNO. 24

CURRENT NACA REPORTS
NACA TN 2700

RECIPROCITY RELATIONS IN AERODYNAMICS.
Max. A. Heaslet and John R. Spreiter. May 1952.
38p. diagrs. (NACA TN 2700)

Reserve-flow theorems in aerodynamics are shown
to be based on the same general concepts involved in
many reciprocity theorems in the physical sciences.
reciprocal theorems for both steady and unsteady
motion are found as a logical consequence of this
approach. No restrictions on wing plan form or
: flight Mach number are made beyond those required
In tinearized compressible-flow analysis. A number
$ examples are listed, including general integral
r. theorems for lifting, rolling, and pitching wings and
for wings in nonuniform downwash fields. Corre-
Sspondence is also established between the build-up
af circulation with Lime of a wing starting impulsively
from rest and the build-up of lift of the same wing
moving in the reverse direction into a sharp-edge
gust. -


i NACA TN 2728

ii EXPERIMENTS TO DETERMINE NEIGHBORHOOD
S REACTIONS TO LIGHT AIRPLANES WITH AND
S WITHOUT EXTERNAL NOISE REDUCTION. Fred S.
S Elwell, Aeronautical Research Foundation. May
1952. 75p. diagrs., maps, photos., 12 tabs. (NACA
TN 2728)

Experiments to determine neighborhood reactions to
the noise of light airplanes with and without noise-
reduction equipment were conducted at a number of
sites which might be convenient locations for landing
strips within the metropolitan area of Boston, Mass.
Two standard airplanes and two airplanes modified by
reduction gears, four-bladed propellers, and engine
exhaust silencers were used. Flights were made
close to residential properties of varying income
levels, population densities, and proximity to trade
centers in order to determine whether the degree of
noise reduction previously found to be aerodynami-
cally and structurally practicable produced a signifi-
cant reduction in neighborhood objections to such air-
craft operations.


N-3074B*

INDEX OF NACA TECHNICAL PUBLICATIONS,
1949-MAY 1951. (Supplement to the index of NACA
technical publications, 1915-1949). viii, 201p.
(NACA)


i ftfte -or 'Aeronautics


rrac

N .t JUNE 3, 1952

This is'the s! element to the Index of NACA
Techn~Ilu-PabH nations, 1915-1949 and covers docu-
ments issued through May 1951. There is a classi-
fied listing of the subject categories, a chronological
list of publications under each subject category, an
alphabetical index to the subject categories, and an
author index.


BRITISH REPORTS

N-14293?

Royal Aircraft Establishment (Gt. Brit.)
THE EFFECT OF INDUCED VELOCITY VARIATION
ON HELICOPTER ROTOR DAMPING IN PITCH OR
ROLL. G. J. Sissingh. November 1951. 16p.
diagrs. (RAE Tech. Note Aero 2132)

A continuation of NACA TN 2136 by Amer on the aero-
dynamic damping of a rotor with centrally arranged
flapping hinges in a steady pitching or rolling motion.
Considers the effect of variation in induced velocity
due to changes in distribution of thrust around the
rotor disk. Results agree favorably with flight re-
sults given in Amer's report. The rotor damping
primarily depends on two quantities: (1) the ratio of
collective pitch to the thrust coefficient solidity
ratio, and (2) the tip-speed ratio x rotor angle of
attack collective pitch.


N-14418*

Aeronautical Research Council (Gt. Brit.)
APPROXIMATE TWO-DIMENSIONAL AEROFOIL
THEORY. PART VI. AEROFOILS WITH HINGED
FLAPS. S. Goldstein and J. H. Preston. August 2,
1945. 42p. diagrs., 4 tabs. (ARC CP 73; ARC 8877)

The calculation of the velocity at the surface and of
other aerodynamic properties, especially the hinge
moment, of an airfoil with a hinged flap is considered
using a simple theory. It is shown in the appendix
how more accurate results may be obtained.


N-14655*

National Gas Turbine Establishment (Gt. Brit.)
A THEORETICAL NOTE UPON THE MECHANISM OF
DEPOSITION IN TURBINE BLADE FOULING. M. C.
G. Smith. February 1952. 40p. diagrs. (NGTE
Memo. M. 145)

The three principal modes by which deposition is
likely to occur, namely by direct impact, vapor dif-


V


AVAILABLE ON LOAN ONLY.
ADDRESS REQUESTS FOR DOCUMENTS TO NACA, 1724 F ST., NW., WASH I NGTON 25, D. C., CITING CODE NUMBER, TITLE AND AUTHOR.




UNIVERSITY OF FLORIDA


3 1262 09079 7522
NACA
2 RESEARCH ABSTRACTS N0.24


fusion, and Brownian movement of small liquid or
solid particles, are considered in detail. Data are
presented from which it is possible to estimate the
quantity of fouling matter reaching the surface pro-
vided its state, concentration, and, in particular, the
size of the particles, are known.


N-14703*

Royal Aircraft Establishment (Gt. Brit.)
THE MAGNETIC PROPERTIES OF SOME DUCTILE
OR MACHINABLE PERMANENT MAGNET ALLOYS.
E. C. Railton. November 1951. 0lp. diagr., tab.
(RAE Tech. Note EL. 29)

The magnetic properties of certain Cu-Ni-Fe and
Co-Fe-V alloys have been measured. The alloys are
respectively ductile after heat treatment and machin-
able before heat treatment, and may have application
as permanent magnets in aircraft electrical instru-
ments. The Cu-Ni-Fe alloy had magnetic properties
that approached those sought. The Co-Fe-V alloy
began to approach published claims for it but is, in
general, less useful.


N-14704 *

Aeroplane and Armament Experimental Establish-
ment (Gt. Brit.) PRECESSION RATE TRIALS OF
THE GYRO UNITS OF THE GYRO-MAGNETIC COM-
PASSES MARK 4F and 4B. March 4, 1952. 7p.
9 tabs. (AAEE Rept. A.A.E.E./Inst/84)

Trials were made to determine the precession rates
of the gyros of the GM 4F and GM 4B units. The
trial showed that three out of the eight gyro units
tested had precession rates in excess of the specifi-
cation.


N-14705*

Royal Aircraft Establishment (Gt. Brit.)
FRICTION TESTS AT HIGHER TEMPERATURES IN
AN INVESTIGATION OF "SCHMELZFLUSSSCHMIE-
RUNG". (Gleitversuche bei hoheren temperature
zur untersuchung der "schmelzflussschmierung'").
E. Siebel. November 1951. 53p. diagrs., photos.,
7 tabs. (RAE Library Trans. 391. Trans. from
Staatliches Materialprufungsamt, Berlin)

Reports tests of materials for ammunition and gun
barrels. Some materials showed a fall of friction
due to surface melting when rubbing at high speeds
and pressures. This was investigated. Methods of
separating the rubbing surfaces by a layer which does
not produce the low friction associated with this
"melt lubrication" were investigated. Measurements
were made of the coefficients of friction, tempera-
tures and load carrying capacities of the materials.


N-14707*

Royal Aircraft Establishment (Gt. Brit.)
HELICOPTER BEHAVIOUR IN THE VORTEX RING
CONDITIONS. Wm. Stewart. November 1951. 15p.
diagrs., tab. (RAE Tech. Note Aero 2131)


A region of roughness, associated with the air flow
conditions of the vortex-ring state, occurs when a
helicopter is operating in vertical or near vertical
descents in the range of about 500 and 1500 ft,'min.
The turbulent circulating air and the rapid changes
in local velocities in this flow pattern can cause
serious helicopter handling difficulties. This could
cause concern in a slow steep approach, particularly
under instrument flying conditions. This report de-
scribes flight experience in the vortex-ring condi-
tions with the Sikorsky R-4B, R-6 and S-51, Bell 47
and the Bristol 171 helicopters.


N-14709 *

Royal Aircraft Establishment (Gt. Brit.)
SOME CURVES FOR USE IN CALCULATIONS OF
THE PERFORMANCE OF CONICAL CENTREBODY
INTAKES AT SUPERSONIC SPEEDS AND AT FULL
MASS FLOW. L. E. Fraenkel. December 1951.
33p. diagrs., 2 tabs. (RAE Tech. Note Aero 2135)

Presents curves of a number of parameters which
frequently occur in calculations of the performance
of conical centerbody intakes at supersonic speeds
and full mass flow. These parameters follow direct-
ly from the theoretical supersonic flow past cones.
Semicone angles of 15, 20, 22.5, 25 and 30
are considered, and the range of free stream Mach
number is approximately 1.3 to 3.0.


N-14710*

National Gas Turbine Establishment (Gt. Brit.)
A PHENOMENOLOGICAL THEORY OF UNIAXIAL
DEFORMATION. A. Graham. December 1951. 30p.
diagrs. (NGTE R. 94)

Previous theories are briefly reviewed and a form of
the Nutting equation in which the constants are ex-
pressed as functions of temperature is shown to avoid
some of the difficulties of theories which assume
existence of an equation of state in terms of stress,
strain, straining rate, and temperature. A linear
theory is developed in which deformation is repre-
sented as a Boltzmann superposition of increments of
creep due to increments of load. The resulting super-
position integral is not an equation of state in the
above-mentioned terms. It directly predicts behavior
under various conditions of loading. The theory is
extended to cover temperature and apparent changes
in material constants.


NACA-Langley 6-3-52 4000




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