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

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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:
AA00009235:00002

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Nati j advisory Committee For Aeronautics



/ 5 Research Abstracts
NO. 2 DEC 9 .355 APRIL 30, 1953


CURRENT N A REPORTS


NACA Rept. 1085

DISCUSSION OF BOUNDARY-LAYER CHARACTER-
ISTICS NEAR THE WALL OF AN AXIAL-FLOW
COMPRESSOR. Artur Mager, John J. Mahoney and
Ray E. Budinger. 1952. ii, 20p. diagrs., photo., tab.
(NACA Rept. 1085. Formerly RM E51H07)

Boundary-layer velocity profiles on the casing of an
axial-flow compressor behind the guide vanes and
rotor were measured and resolved into two compo-
nents: along the streamline of the flow and perpen-
dicular to it. Boundary-layer thickness and the de-
flection of the boundary layer at the wall were the
generalizing parameters. By use of these results and
the momentum-integral equations, the characteristics
of boundary layer on the walls of axial-flow compres-
sor are qualitatively discussed. Important param-
eters concerning secondary flow in the boundary layer
appear to be turning of the flow and the product of
boundary-layer thickness and streamline curvature
outside the boundary layer. Two types of separation
are shown to be possible in three dimensional
boundary layer.



NACA Rept. 1088

THEORETICAL DAMPING IN ROLL AND ROLLING
MOMENT DUE TO DIFFERENTIAL WING
INCIDENCE FOR SLENDER CRUCIFORM WINGS
AND WING-BODY COMBINATIONS. Gaynor J
Adams and Duane W. Dugan. 1952. ii, I Ip. diagrs.
(NACA Rept. 1088. Extends analysis of TN 2270)

A method of analysis based on slender-wing theory
is developed to investigate the characteristics in roll
of slender cruciform wings and wing-body combina-
tions. The method makes use of the conformal
mapping processes of classical hydrodynamics which
transform the region outside a circle and the region
outside an arbitrary arrangement of line segments
intersecting at the origin. The method of analysis
may be utilized to solve other slender cruciform
wing-body problems involving arbitrarily assigned
boundary conditions.


NACA TN 2923

STUDY OF MOTION OF MODEL OF PERSONAL-
OWNER OR LIAISON AIRPLANE THROUGH THE
STALL AND INTO THE INCIPIENT SPIN BY MEANS
OF A FREE-FLIGHT TESTING TECHNIQUE Ralph
W. Stone, Jr William G. Garner and Lawrence J.
Gale. April 1953 28p. -diagrs., photos., tad
INACA TN 2923)

This paper presents the motion of a dynamic model
through the stall and into the incipient spin. The
results indicate that, after the initial stall, the model
became unstallea. inverted, and assumed very low
angles of attack before restalling and entering the
incipient spin Altitude loss and angular velocities
were relatively small during the early part of the
motion and indicated that this time would be the
optimum time to terminate the motion by control
mo ement


NACA TN 2925

LIFT DEVELOPED ON UNRESTRAINED RECTAN-
GULAR WINGS ENTERING GUSTS AT SUBSONIC
AND SUPERSONIC SPEEDS Harvard Lomax.
April 1953. 44p. diagrs 2 tabs INACA TN 2925)

Lift forces induced by a vertical gust are estimated
on the basis of theoretical calculations The effects
of pitching and wing bending are neglected and only
Aings of rectangular plan form are considered.
However, the eliffects of Mach number (from 0 to 2)
and aspect ratio 12 to z) are included, and solutions
are given by means of which the response to gusts
having arbitrary streanwise gradients can be cal-
culated. Results are presented for sharp-edged
and triangular gusts and various wing-air density
ratios.


NACA TN 2931

A METHOD FOR DETERMINING CLOUD-DROPLET
IMPINGEMENT ON SWEPT WINGS Robert G
Dorsch and Rinaldo J. Brun April 1953. 29p
diagrs. (NACA TN 29311

The general effect of wing sweep on cloud-droplet
trajectories about swept wings of high aspect ratio
mo ing at subsonic speeds is discussed. A method
of computing droplet trajectories about yawed
cylinders and swept wings is presented, and illustra-
tive droplet trajectories are computed A method
of extending two-dimensional calculations of droplet
impingement on nonssept wings to swept wings is
presented. It is shown that the extent of impinge-


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2


ment of cloud droplets on an airfoil surface, the
total rate of collection of water, and the local rate
of impingement per unit area of airfoil surface can
be found for a swept wing from two-dimensional data
for a nonswept wing. The impingement on a swept
wing is obtained from impingement data for a non-
swept airfoil section which is the same as the section
in the normal plane of the swept wing by calculating
all dimensionless parameters with respect to flow
conditions in the normal plane of the swept wing.


NACA RM E52L23a

FREE FALL AND EVAPORATION OF n-OCTANE
DROPLETS IN THE ATMOSPHERE AS APPLIED TO
THE JETTISONING OF AVIATION GASOLINE AT
ALTITUDE. Herman H. Lowell. April 1953. 25p.
diagrs. (NACA RM E52L23a)

In connection with proposed rapid jettisoning of
aviation gasoline at altitude, a theoretical study was
made of the free fall and evaporation of n-octane
droplets in the atmosphere; n-octane was selected
for study because of the expected similarity of over-
all evaporation behavior of n-octane and gasoline.
It was concluded that gasoline (or n-octane) droplets
larger than 2000 microns in diameter would be
unstable; terminal speeds and Reynolds numbers
were obtained for droplets not larger than 2000
microns at altitudes to 11,000 feet. The motion
data were used in the calculation of n- octane
evaporation rates under various conditions. It was
found that a droplet having an original diameter of
2000 microns would fall about 4000 feet from 6000
feet under NACA standard atmosphere conditions
before coming virtually to rest. Finally, it was
concluded that temperature effects are of paramount
importance; at highest air temperatures a 1000-foot
ground clearance would probably be adequate to
prevent ground contamination, whereas at lowest
air temperatures only an atomizing spray arrange-
ment would prevent ground contamination,
irrespective of ground clearance.



BRITISH REPORTS


N-21216*

Aeronautical Research Council (Gt. Brit.)
ABSTRACTS OF PAPERS PUBLISHED EXTER-
NALLY. February 1951. 15p. (ARC R & M 2722)

This report contains abstracts of a group of reports
recommended for external publication by the Aero-
nautical Research Council. These reports cover a
variety of subjects relating to aeronautics.


N-21712*

Royal Aircraft Establishment (Gt. Brit.)
INTERNAL FRICTION AND GRAIN BOUNDARY
VISCOSITY OF SILVER AND OF BINARY SILVER
SOLID SOLUTIONS. S. Pearson. January 1953.
22p. diagrs., 4 tabs. (RAE Met. 71)


NACA
RESEARCH ABSTRACTS NO.42


Measurements have been made of the variation of
internal friction with temperature for spectro- .
scopically pure silver and for a series of solid so-
lutions of silver with cadmium, indium, and tin,
using a Ke type torsion pendulum apparatus. Some
experiments have also been made to investigate the
effect of nonmetallic impurity on grain boundary
relaxation in silver. The effect of the alloying
elements is to increase the grain boundary viscosity
and to raise the activation energy for grain boundary
relaxation from 22, 000 cal/mole for pure silver to
43, 000 cal/mole for the solid solutions, the same
value being obtained, within the limits of experi-
mental error, for all the alloying elements and for
all the solute concentrations investigated. The re-
sults of the experiments show exactly the same trend
as those obtained previously for a similar series of
copper solid solutions. They are in agreement with
the general theory of grain boundary relaxation
developed by Zener and K9 but do not seem to be
in agreement with either of the mechanisms so far
put forward to explain grain boundary slip.


N-21717*

Royal Aircraft Establishment (Gt. Brit.)
CURVES FOR ESTIMATING THE WAVE DRAG OF
SOME BODIES OF REVOLUTION, BASED ON
EXACT AND APPROXIMATE THEORIES. L. E.
Fraenkel. August 1952. 15p. diagrs. (RAE
Tech. Note Aero 2184)

Curves are presented for estimating the wave drag,
at zero incidence, of forebodies and afterbodies
having straight and parabolic profiles. The after-
bodies are assumed to lie behind an infinitely long
cylindrical body. The curves are based on a limited
number of exact and second-order solutions which
have been generalized by appealing to the supersonic-
hypersonic similarity law and to slender body and
quasi-cylinder solutions.


N-21719*

Royal Aircraft Establishment (GI. Brit.)
ON THE GEOMETRICAL CHANGES THAT OCCUR
WHEN WINGS ARE ROTATED ABOUT AXES THAT
ARE NEARLY NORMAL TO THE WINGS. C. H. E.
Warren. November 1952. 10p. diagrs. (RAE
Tech. Note Aero 2212)

This note merely presents the geometrical relation-
ships that occur when the wings of an aircraft are
rotated about axes that are nearly normal to the
planes of the wings. Only elementary, but somewhat
cumbersome, trigonometry is involved, but the re-
lationships do depend upon precise definitions of the
angles of sweepback and dihedral.








NACA
RESEARCH ABSTRACTS NO.42


N-21743*

Aeronautical Research Council (Gt. Brit )
NOTE ON THE WAKES BEHIND BODIES MOVING
AT HIGH MACH NUMBER. D. W. Holder.
March 8, 1952. lip. photos., diagrs., tab. (ARC
14, 720; FM 1693)

Schlieren photographs are presented to provide ex-
amples of apparently periodic, or otherwise unusual,
flow in the wakes of bodies moving at high Mach
number.



UNPUBLISHED PAPERS


N-22547 *

FUSELAGE SHOCK ABSORBERS. (Amortizatory
shassi). 13p. diagrs. (Trans. from Construction
of Airplanes, by M. N. Shulzhenko, 1949, p.403-
410).

This report describes the principles of operation
and construction of liquid-air shock absorbers.


N-22618 *

THE HYDRODYNAMIC THEORY OF HEAT
EXCHANGE AND ITS APPLICATION TO THE
EXTERNAL PROBLEM OF THE BOUNDARY
LAYER. (0 svyazi obobshchennykh integral'nykh
sootnoshenii s gidrodinamicheskoi teoriei teploob-
mena i o ee prilozhenii k raschetu teploobmena v
usloviyakh vneshnei zadachi). L. I. Kudryashev.
lip. (Trans. from Akademiia Nauk SSSR, Izvestiia,
Otdelenie Tekhnicheskikh Nauk, no.11, 1951, p.1682-
1688).

A connection is established between the generalized
integral relations for the hydrodynamic and thermal
boundary layers, both laminar and turbulent, and
the hydrodynamic theory of heat exchange. The
application to the computation of the heat exchange
permits solving the problem of the computation of
the heat-transfer coefficient in the case of the flow
about a flat plate for any law of distribution of the
velocities and temperatures in the boundary layer.


N-22619'

THE OXIDIZING NITRATION OF NITROSO COM-
POUNDS AND ARYLHYDROXYLAMINES.
(Okislitel'nole nitrovanie aromaticheskikh nitrozo-
soedinenili i arilgidroksilaminov). A. I. Titov and
N. G. Laptev. EXPERIMENTAL PROCEDURE, by
A. I. Titov, N. G. Laptev and A. N. Baryshnikova.
1ip, (Trans. from Zhurnal Obshchei Khimii, v. 18,
pt. 1, 1948, p. 741-748).

It is shown that the aromatic nitroso compounds and
arylhydroxylamines under the action of nitric acid
containing nitrogen oxides may undergo very differ-
ent transformations leading to the formation of a


3


mixture of the corresponding nitro compounds, diazo
compounds, p-dinitroso compounds, p-nitrosodiaryl-
hydroxylamines, oxalic acid, and nitrophenols con-
taining hydroxyl in the para position relative to the
place previously occupied by the nitroso group.
Mechanisms for these reactions are proposed.
Detailed procedure is given for performing the
nitration.


N-22620*

ON THE MECHANISM OF THE NITRATION OF
AROMATIC COMPOUNDS BY A SULFURO-NITRIC
ACID MIXTURE AND OTHER ENERGETICALLY
NITRATING MEANS. (0 mekhanizme nitrovaniya
aromaticheskikh soedinenii sernoazotnoi smes'yu i
drugimi energichno nitruyushchimi sredatvani).
A. I. Titov. 13p. (Trans. from Zhurnal Obshchei
Khimii, v. 18, pt. 1, 1948, p. 733-740).

The nitration by nitric acid of benzene and other
aromatics possessing a nuclear affinity equal to or
less than that of benzene, occurs principally through
an intermediate interaction with various forms of
nitrogen dioxide only at low concentrations of the
acid. The authors attempt to explain this phenome-
non.


NACA-Langley 4-30-53 -4000






UNIVERSITY OF FLORIDA




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