Research abstracts

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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:
AA00009235:00084

Related Items

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


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Committee for Aeronautics


racts


TN 2484
Ct 0 COMPRESSIBILITY ON THE FLOW
.TWO -DIENSIONAL BUMP. W. F. Lindsey
d N. Daley. April 1952. 34p. diagrs.,
(MA ACA TN 2484. Formerly RM L6Kl2b)
,-'..ttes has been conducted to determine ex-
|fly the effects of compressibility on the
.aump and toscompare the experimentally
results with theory. Pressure measure-
hlieren photographs were made of the
i.ibumps having thickness-chord ratios of
Sat Mach numbers between 0.20 and





TO THE PREDICTION OF THE FRE-
UTION OF GUST LOADS ON AIR-
blMAL OPERATIONS. Harry Press.
b4 ;p. diagrs., 2 tabs. (NACA TN 2660)


the prediction of the gust-load history
i: service 'operations, the statistical
fmto variables and probability distri-
u,#ted to the "sharp edge gust" formula.
A l.erived for the frequency distribu-
-. 10t4\n terms of distributions of the re-
.00such as effective gust velocity and air-
onil are obtained under assumptions
reasonable on the basis of present prac-
A',:eheareh. The results are applied in an
oK' he predicted load experience is comn-
iMp mrailable flight loads data for this case.



:,,4 OF DIAGONAL TENSION. PART 1 -
IWhO,! ANALYSIS. Paul Kuhn, James P.
Ib aid L. Ross Levin. May 1952. v, 131p.
i4: oto. ($ACA TN 2661)
**
laquy published methods for stress and strength
rjBtat plane and curved shear webs working in
Al.teinslon ar.e presented as a unified method.
Itttment .is sufficiently comprehensive and de-
ttc make the paper self-contained. Part I dis-
p the. ateory and methods for calculating the
p anmd shear deflections of web systems as
F4 rgths of the web, the stiffeners, and
lfIc .Paz:t.., published separately, presents
bW|M|zG|A' v'd6vence.


NACA TN 2662


A SUMMARY OF DIAGONAL TENSION. PART II -
EXPERIMENTAL EVIDENCE. Paul Kuhn, James P.
Peterson and L. Ross Levin. May 1952. ii, 81p.
diagrs., photos., 8 tabs. (NACA TN 2662)

Methods of analyzing web systems working in diago-
nal tension have been given in Part I of this paper.
Part II presents the experimental evidence.


NACA TN 2663


THE GUST AND GUST-LOAD EXPERIENCE OF A
TWIN-ENGINE LOW-ALTITUDE TRANSPORT AIR-
PLANT IN OPERATION ON A NORTHERN TRANS-
CONTINENTAL ROUTE. Harry Press and Robert L.
McDougal. April 1952. 33p. diagrs., 8 tabs. (NACA
TN 2663)

An analysis of the gust and gust-load experience of
a low-altitude transcontinental transport airplane,
based on 834 hours of VGH record, is presented. The
relation of gust experience to airspeed, altitude,
season of the year, and flight condition is considered.
An estimate of the over-all gust history for the
present type of operations is derived from a synthesis
of the VGH data and available V-G data.


NACA TN 2674


SOME EXPERIMENTS ON VISUALIZATION OF FLOW
FIELDS BEHIND LOW-ASPECT-RATIO WINGS BY
MEANS OF A TUFT GRID. John D. Bird and Donald
R. Riley. May 1952. 32p. photos., diagrs., tab.
(NACA TN 2674)

A technique for obtaining a physical picture of the
flow behind lifting surfaces is described wherein the
action of a large number of tufts of uniform length
attached to a wire grid are photographed from far
downstream. This procedure yields, with a minimum
of labor, an approximate vector plot of the flow field
in a plane normal to the air stream. The flow fields
behind a rectangular wing and several triangular
wings were investigated through the angle-of-attack
range. The effects of tip-control deflection, side-
slip, and oscillation in sideslip on the flow field be-
hind a 60 triangular wing were also determined.


57: 4


100Q4"NM S TO NACA, 174 F ST. Nw., WASHINGTON 25, D. C, CaTING CODE NUMBER ABOVE EACH TITLE,


. .. ,. .








NACA
2 RESEARCH ABSTRACTS NO.23


NACA TN 2683

SURVEY OF PORTIONS OF THE CHROMIUM-
COBALT-NICKEL-MOLYBDENUM QUATERNARY
SYSTEM AT 1200 C. Sheldon Paul Rideout and
Paul A. Beck, University of Notre Dame. April
1952. 81p. diagrs., photos., 20 tabs. (NACA TN
2683)

A survey was made of portions of the chromium-
cobalt-nickel-molybdenum quaternary system at
1200 C by means of microscopic and X-ray diffrac-
tion studies. Since the face-centered cubic (alpha)
solid solutions form the matrix of almost all practi-
cally useful high-temperature alloys, the solid solu-
bility limits of the quaternary alpha phase were de-
termined up to 20 percent molybdenum. The com-
ponent cobalt-nickel-molybdenum, chromium-cobalt-
molybdenum, and chromium-nickel-molybdenum
ternary systems were also studied. The survey of
these systems was confined to the determination of
the boundaries of the face-centered cubic (alpha)
solid solutions and of the phases coexisting with alpha
at 1200 C.


NACA TN 2688

THREE-DIMENSIONAL SUPERSONIC NOZZLES AND
INLETS OF ARBITRARY EXIT CROSS SECTION.
John C. Evvard and Stephen H. Maslen. April 1952.
12p. diagrs. (NACA TN 2688)

A method is presented for obtaining three dimen-
sional unsymmetric supersonic nozzles and inlets
from known axisymmetric flows. Streamlines bound-
ing the desired exit shape are traced through the
known basic flow solution to give the required unsym-
metric wall contours. Several examples are given.


NACA TN 2690

CONDENSATION OF AIR IN SUPERSONIC WIND
TUNNELS AND ITS EFFECTS ON FLOW ABOUT
MODELS. C. Frederick Hansen and George J.
Nothwang. April 1952. 49p. photos., diagrs.
(NACA TN 2690)

Condensation of air in supersonic wind tunnels is
investigated. Theoretical limits of the threshold of
condensation are calculated and compared with ex-
periment. Test results are presented which indicate
the effectiveness of water vapor, carbon dioxide,
and silica gel as condensation nuclei in supersatur-
ated air. The properties of a partially condensed
supersonic air stream are estimated and the effects
of condensation phenomena in flow about models are
examined.


NACA TN 2693

A THEORY AND METHOD FOR APPLYING
INTERFEROMETRY TO THE MEASUREMENT OF
CERTAIN TWO-DIMENSIONAL GASEOUS DENSITY
FIELDS. Walton L. Howes and Donald R. Buchele.
April 1952. 46p. diagrs. (NACA TN 2693)


A theory and method are developed for applying inter-
ferometry to the measurement of certain two dimen-
sional gaseous density fields. The theory includes
effects of optical refraction upon the observed inter-
ference pattern. Expressions for the relative density-,
difference and optical distortion corresponding to an
observed interference-fringe shift are derived in
exact form and then in the form of power series ap-
proximations. An evaluation procedure is outlined
and applied in the determination of the density field
in a boundary layer formed by supersonic air flow
along a flat plate.


NACA TN 2696

A FUNDAMENTAL STUDY OF THE MECHANISM BY
WHICH HYDROGEN ENTERS METALS DURING
CHEMICAL AND ELECTROCHEMICAL PROCESSING.
L. D. McGraw, C. A. Snavely, H. L. Moore, P. T.
Woodberry and C. L. Faust, Battelle Memorial
Institute. April 1952. ii, 43p. photos., diagr., 6
tabs. (NACA TN 2696)

Through the correlation of several known methods of
controlling entry and exit of hydrogen in steel with
the known chemical behavior of atomic and molecular
hydrogen suitable reagents were found which increase
or, for the first time, significantly decrease hydro-
gen permeability and embrittlement of steels during
cathodic pickling and plating operations. This suc-
cesful correlation was an important step toward ar-
riving at the mechanism of hydrogen entry into steel.
It is proposed that entry is through the direct forma-
tion of metal hydrides (intermetallic compounds) or
solid solutions of hydrogen in metal at the instant of
hydrogen discharge and that exit is the decomposition
of metal hydrides or of solid solutions of hydrogen in
metal.


NACA TN 2701

A SURVEY OF THE AIRCRAFT-NOISE PROBLEM
WITH SPECIAL REFERENCE TO ITS PHYSICAL
ASPECTS. Harvey H. Hubbard. May 1952. 41p.
diagrs., photos. (NACA TN 2701)

This paper presents brief discussions on three gen-
eral phases of the aircraft-noise problem. The ef-
fects of noise are discussed as a background for the
reader and as a basis for discussion of the other
material. A description of the physical characteris-
tics of aircraft noise and some ways of protection
from noise are also included, along with a limited
bibliography of research work applying to the aircraft-
noise problem.


NACA RM E52B20

INTERNAL-FILM-COOLING EXPERIMENTS WITH
2- AND 4-INCH SMOOTH-SURFACE TUBES AND
GAS TEMPERATURES TO 2000 F. George R.
Kinney. April 1952. 27p. diagrs., 2 tabs. (NACA
RM E52B20)


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S"NACA
i R RESEARCH H


:- -+- An experimental investigation of internal-liquid-film
Cooling was conducted in 2- and 4-inch-diameter
smooth-surface tubes with hot air flows at 800 to
-2000 F and Reynolds numbers from 220,000 to
: 1'1I00,000. The cqolant was water at flows of 0. 8 to
S 12 percent of air flow. Greater cooling effectiveness
l was obtained than in a previous investigation with a
I,," .rough-surface tube. When coolant flows were large
Plenough, film disturbances occurred which reduced
S::'cooling effectiveness in the same manner in both 2-
,.: and 4-inch tubes. All data were generalized by means
V.l::'..of heat transfer correlation and data obtained over a
,-rantge. of coolant flows in a form which facilitates the
1 .estimation of the flow of film coolant required to cool
a ,*? ,length of tube when the temperature and flow of hot
aimil:: aes. are known.
|;.ji..*'*'" .+

tl.. ACA RM L52B18a

SBIBLIOGRAPHY OF NACA PAPERS ON ROTATING-
ry- WING AIRCRAFT, JANUARY 1952. Alfred Gessow.
:' March 1952. 13p. (NACA RM L52B18a. Formerly
t41M LJSO)

L'. A bibliography of NACA papers on rotating-wing air-
S craft issued up to January 1952 is presented. The
list of papers is subdivided for ready reference
lm. ruder appropriate subject headings, and the titles
i are listed chronologically within each subject.


BRITISH REPORTS



l.... '. -14040*

VSC *'""Royal Aircraft Establishment (Gt. Brit.)
.....THE MEASUREMENT OF HEAT TRANSFER AND
8 SKIN FRICTION AT SUPERSONIC SPEEDS.
PART HI MEASUREMENTS OF OVERALL HEAT
;:1 .. TRANSFER AND OF THE ASSOCIATED BOUNDARY
I:;, LAYERS ON A FLAT PLATE AT MI = 2.43. R. J.
i Monaghan and J. R. Cooke. December 1951. 64p.
: diagrs., photos., 3 tabs. (RAE Tech. Note Aero
S 2129)

pF A mean value of 0.906 was obtained for temperature-
Srecovery factor and the over-all heat transfer meas-
rf. :"urements from plate to stream agreed well with other
S published results. There was some forward move-
.. ment of the boundary-layer transition, a variation in
:H1:1 -the exponent of the turbulent velocity distribution and
an increase in displacement thickness with heat
S transfer. However, no decrease in skin friction
below its zero heat transfer value was found.


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UNPUBLISHED PAPERS


N-8810"

CONTRIBUTION TO THE WING THEORY FOR
SLIGHTLY INHOMOGENEOUS PARALLEL FLOW.
(Beitrag zur Theorie des Tragflugels in schwach
inhomogener Parallelstromung). F. Vandrey. March
1952. 12p. diagrs. (Trans. from Zeitschrift fur
angewandte Mathematik und Mechanik, v. 20, no. 3,
June 1940, p. 148-152).

Calculation of lift distribution of a wing in a flow with
a velocity varying from point to point is traced back
to calculation of the lift distribution of a wing of
equal chord distribution with an additional twist in a
homogeneous parallel flow. The twist is determined
from the condition of equivalent pressure on both
sides of a surface of constant basic velocity. Pre-
supposition for applicability of the method is the con-
dition that the velocity of the basic flow does not
vary greatly in the direction normal to the wind.


N-12159*

THE PROBLEM OF FLOW AROUND A BODY IN IN-
COMPRESSIBLE POTENTIAL FLOWS. PART U.
(Das Umstro6mungsproblem bei inkompressiblen
Potentialstr6mungen). F. Riegels. April 1952. 31p.
diagrs., 10 tabs. (Trans. from Ingenieur-Archiv,
v. 17, no. 1-2, 1949, p. 94-106).

For bodies of moderate thickness and camber but
otherwise arbitrary shape, a theory is developed
which permits determination of the flow velocity, the
force, and the moment with the aid of source and
vortex distributions on a straight-line segment of the
length of the largest chord of the body.


ABSTRACTS N0.23


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