queries.txt

.I 001
.W
what similarity laws must be obeyed when constructing aeroelastic models
of heated high speed aircraft .
.I 002
.W
what are the structural and aeroelastic problems associated with flight
of high speed aircraft .
.I 004
.W
what problems of heat conduction in composite slabs have been solved so
far .
.I 008
.W
can a criterion be developed to show empirically the validity of flow
solutions for chemically reacting gas mixtures based on the simplifying
assumption of instantaneous local chemical equilibrium .
.I 009
.W
what chemical kinetic system is applicable to hypersonic aerodynamic
problems .
.I 010
.W
what theoretical and experimental guides do we have as to turbulent
couette flow behaviour .
.I 012
.W
is it possible to relate the available pressure distributions for an
ogive forebody at zero angle of attack to the lower surface pressures of
an equivalent ogive forebody at angle of attack .
.I 013
.W
what methods -dash exact or approximate -dash are presently available
for predicting body pressures at angle of attack.
.I 015
.W
papers on internal /slip flow/ heat transfer studies .
.I 018
.W
are real-gas transport properties for air available over a wide range of
enthalpies and densities .
.I 022
.W
is it possible to find an analytical,  similar solution of the strong
blast wave problem in the newtonian approximation .
.I 023
.W
how can the aerodynamic performance of channel flow ground effect
machines be calculated .
.I 026
.W
what is the basic mechanism of the transonic aileron buzz .
.I 027
.W
papers on shock-sound wave interaction .
.I 029
.W
material properties of photoelastic materials .
.I 031
.W
can the transverse potential flow about a body of revolution be
calculated efficiently by an electronic computer .
.I 032
.W
can the three-dimensional problem of a transverse potential flow about
a body of revolution be reduced to a two-dimensional problem .
.I 033
.W
are experimental pressure distributions on bodies of revolution at angle
of attack available .
.I 034
.W
does there exist a good basic treatment of the dynamics of re-entry
combining consideration of realistic effects with relative simplicity of
results .
.I 035
.W
has anyone formally determined the influence of joule heating,  produced
by the induced current,  in magnetohydrodynamic free convection flows
under general conditions .
.I 039
.W
why does the compressibility transformation fail to correlate the high
speed data for helium and air .
.I 040
.W
did anyone else discover that the turbulent skin friction is not over
sensitive to the nature of the variation of the viscosity with
temperature .
.I 041
.W
what progress has been made in research on unsteady aerodynamics .
.I 049
.W
what are the factors which influence the time required to invert large
structural matrices .
.I 050
.W
does a practical flow follow the theoretical concepts for the
interaction between adjacent blade rows of a supersonic cascade .
.I 051
.W
what is a single approximate formula for the displacement thickness of
a laminar boundary layer in compressible flow on a flat plate .
.I 052
.W
how is the design of ring or part ring wings by linear theory affected
by thickness .
.I 053
.W
what application has the linear theory design of curved wings .
.I 054
.W
what is the effect of cross sectional shape on the flow over simple
delta wings with sharp leading edges .
.I 055
.W
papers on flow visualization on slender conical wings .
.I 056
.W
what size of end plate can be safely used to simulate two-dimensional
flow conditions over a bluff cylindrical body of finite aspect ratio .
.I 057
.W
to find an approximate correction for thickness in slender thin-wing
theory .
.I 058
.W
how do interference-free longitudinal stability measurements (made
using free-flight models) compare with similar measurements made in
a low-blockage wind tunnel .
.I 059
.W
have wind tunnel interference effects been investigated on a systematic
basis .
.I 061
.W
are there any papers dealing with acoustic wave propagation in reacting
gases .
.I 062
.W
has anyone investigated relaxation effects on gaseous heat transfer to a
suddenly heated wall .
.I 066
.W
are there any theoretical methods for predicting base pressure .
.I 067
.W
does transition in the hypersonic wake depend on body geometry and size
.I 068
.W
how can one detect transition phenomena in boundary layers .
.I 069
.W
how can one detect transition phenomena in hypersonic wakes .
.I 071
.W
has anyone investigated and developed a simple model for the vortex
wake behind a cruciform wing .
.I 072
.W
what is a criterion that the transonic flow around an airfoil with a
round leading edge be validly analyzed by the linearized transonic flow
theory .
.I 074
.W
can the transonic flow around an arbitrary smooth thin airfoil be
analysed in a simple approximate way .
.I 079
.W
what are the details of the rigorous kinetic theory of gases .
(chapman-enskog theory) .
.I 080
.W
has anyone investigated the effect of surface mass transfer on
hypersonic viscous interactions .
.I 081
.W
what is the combined effect of surface heat and mass transfer on
hypersonic flow .
.I 082
.W
what are the existing solutions for hypersonic viscous interactions over
an insulated flat plate .
.I 083
.W
what controls leading-edge attachment at transonic speeds .
.I 084
.W
can the three-point boundary-value problem for the blasius equation
be integrated numerically,  using suitable transformations,  without
iteration on the boundary conditions .
.I 085
.W
what are the effects of small amounts of gas rarefaction on the
characteristics of the boundary layers on slender bodies of revolution .
.I 086
.W
what is the available information pertaining to boundary layers on very
slender bodies of revolution in continuum flow (the ?transverse
curvature  effect) .
.I 087
.W
what is the available information pertaining to the effect of slight
rarefaction on boundary layer flows (the ?slip? effect) .
.I 093
.W
what investigations have been made of the flow field about a body moving
through a rarefied,  partially ionized gas in the presence of a magnetic
field .
.I 094
.W
how is the heat transfer downstream of the mass transfer region effected
by mass transfer at the nose of a blunted cone .
.I 095
.W
to what extent can the available information for incompressible boundary
layers be applied to problems involving compressible boundary layers .
.I 097
.W
to what extent can readily available steady-state aerodynamic data be
utilized to predict lifting-surface flutter characteristics .
.I 098
.W
what are the significant steady and non-steady flow characteristics
which affect the flutter mechanism .
.I 099
.W
is it possible to determine rates of forced convective heat transfer
from heated cylinders of non-circular cross-section,  (the fluid flow
being along the generators) .
.I 100
.W
how much is known about boundary layer flows along non-circular
cylinders .
.I 101
.W
is there any simple,  but practical,  method for numerical integration
of the mixing problem (i.e. the blasius problem with three-point
boundary conditions) .
.I 102
.W
does there exist a closed-form expression for the local heat transfer
around a yawed cylinder .
.I 103
.W
how far around a cylinder and under what conditions of flow,  if any,
is the velocity just outside of the boundary layer a linear function of
the distance around the cylinder .
.I 104
.W
where can i find pressure data on surfaces of swept cylinders .
.I 105
.W
can't the static deflection shapes be used in predicting flutter in
place of vibrational shapes . if so,  can we provide a justification by
means of an example .
.I 106
.W
does the boundary layer on a flat plate in a shear flow induce a
pressure gradient .
.I 107
.W
can the procedure of matching inner and outer solutions for a viscous
flow problem be applied when the main stream is a shear flow .
.I 108
.W
can series expansions be found for the boundary layer on a flat plate in
a shear flow .
.I 109
.W
what possible techniques are available for computing the injection
distribution corresponding to an isothermal transpiration cooled
hemisphere .
.I 110
.W
what is known regarding asymptotic solutions to the exact boundary layer
equations .
.I 111
.W
previous solutions to the boundary layer similarity equations .
.I 112
.W
experimental results on hypersonic viscous interaction .
.I 113
.W
what has been done about viscous interactions in relatively low reynolds
number flows,  particularly at high mach numbers .
.I 114
.W
what role does the effect of chemical reaction (particularly when out of
equilibrium) play in the similitude laws governing hypersonic flows over
slender aerodynamic bodies .
.I 116
.W
how significant is the possible pressure of a dissociated free stream
with respect to the realization of hypersonic simulation in high
enthalpy wind tunnels .
.I 118
.W
do the discrepancies among current analyses of the vorticity effect
on stagnation-point heat transfer result primarily from the
differences in the viscosity-temperature law assumed .
.I 119
.W
how far can one trust the linear viscosity-temperature solution
assumed in some of the analyses of hypersonic shock layer at low
reynolds number .
.I 120
.W
how close is the comparison of the shock layer theory with existing
experiments in the low reynolds number (merged-layer) regime .
.I 121
.W
has anyone explained the kink in the surge line of a multi-stage
axial compressor .
.I 122
.W
have any aerodynamic derivatives been measured at hypersonic mach
numbers and comparison been made with theoretical work .
.I 123
.W
are methods of measuring aerodynamic derivatives available which
could be adopted for use in short running time facilities .
.I 126
.W
what are wind-tunnel corrections for a two-dimensional aerofoil
mounted off-centre in a tunnel .
.I 128
.W
how do kuchemann's and multhopp's methods for calculating lift
distributions on swept wings in subsonic flow compare with each other and with
experiment .
.I 130
.W
what is the present state of the theory of quasi-conical flows .
.I 131
.W
references on the methods available for accurately estimating
aerodynamic heat transfer to conical bodies for both laminar and turbulent
flow .
.I 132
.W
what parameters can seriously influence natural transition
from laminar to turbulent flow on a model in a wind tunnel .
.I 133
.W
can a satisfactory experimental technique be developed for measuring
oscillatory derivatives on slender sting-mounted models in supersonic
wind tunnels .
.I 135
.W
what effect has the boundary layer in modifying the basic inviscid flow
behind the shock,  neglecting effects of leading edge and corner .
.I 136
.W
how does a satellite orbit contract under the action of air drag in
an atmosphere in which the scale height varies with altitude .
.I 137
.W
how is the flow at transonic speeds about a delta wing different
from that on a closely-related tapered sweptback wing .
.I 138
.W
recent data on shock-induced boundary-layer separation .
.I 139
.W
what interference effects are likely at transonic speeds .
.I 140
.W
given complete freedom in the design of an airplane,  what procedure
would be used in order to minimize sonic boom intensity,  and is there a
limit to the degree of minimizing that can be accomplished .
.I 141
.W
can methane-air combustion product be used as a hypersonic test
medium and predict, within experimental accuracies, the results
obtained in air .
.I 142
.W
what is the theoretical heat transfer rate at the stagnation point of a
blunt body .
.I 143
.W
what is the theoretical heat transfer distribution around a hemisphere .
.I 145
.W
has anyone investigated the unsteady lift distributions on finite
wings in subsonic flow .
.I 146
.W
what information is available for dynamic response of airplanes to
gusts  or blasts in the subsonic regime .
.I 147
.W
will forward or apex located controls be effective at low subsonic
speeds and how do they compare with conventional trailing-edge
flaps .
.I 148
.W
given that an uncontrolled vehicle will tumble as it enters an
atmosphere, is it possible to predict when and how it will stop
tumbling and its subsequent motion .
.I 149
.W
what are the effects of initial imperfections on the elastic buckling of
cylindrical shells under axial compression .
.I 150
.W
why does the incremental theory and the deformation theory of plastic
stress-strain relationship differ greatly when applied to stability
problems .
.I 152
.W
basic dynamic characteristics of structures continuous over many spans .
.I 153
.W
is the information on the buckling of sandwich sphere available .
.I 154
.W
can the load deformation characteristics of a beam be obtained with the
material being inelastic and a non uniform temperature being present .
.I 155
.W
what is the effect of an internal liquid column on the breathing
vibrations of a cylindrical shell .
.I 156
.W
experimental techniques in shell vibration .
.I 157
.W
in summarizing theoretical and experimental work on the behaviour of a
typical aircraft structure in a noise environment is it possible to
develop a design procedure .
.I 158
.W
what data is there on the fatigue of structures under acoustic loading .
.I 160
.W
panels subjected to aerodynamic heating .
.I 161
.W
can increasing the edge loading of a plate beyond the critical value for
buckling change the buckling mode .
.I 163
.W
have the effects of an elastic edge restraint been considered in
previous papers on panel flutter .
.I 164
.W
has the solution of the clamped plate problem,  in the classical theory
of bending,  been reduced to two successive membrane boundary value
problems .
.I 165
.W
what data exists on oscillatory aerodynamic forces on control surfaces
at transonic mach numbers .
.I 167
.W
it is not likely that the airforces on a wing of general planform
oscillating in transonic flow can be determined by purely analytical
methods . is it possible to determine the airforces on a single
particular planform, such as the rectangular one by such method .
.I 168
.W
is the problem of similarity for representative investigations of
aeroelastic effects in heated flow as intractable as previous investigations
imply .
.I 169
.W
what is the magnitude and distribution of lift over the cone and the
cylindrical portion of a cone-cylinder configuration .
.I 170
.W
is there any information on how the addition of a /boat-tail/ affects
the normal force on the body of various angles of incidence .
.I 171
.W
what are the aerodynamic interference effects on the fin lift and body
lift of a fin-body combination .
.I 173
.W
what is the effect of initial axisymmetric deviations from circularity
on the non linear (large-deflection) load-deflection response of
cylinders under hydrostatic pressure .
.I 175
.W
are previous analyses of circumferential thermal buckling of circular
cylindrical shells unnecessarily involved or even inaccurate due to the
assumed forms of buckling mode .
.I 176
.W
what papers are there dealing with circumferential buckling either
thermal buckling or due to mechanical loading .
.I 177
.W
what analytical investigations have been made of the stability of
conical shells . how do the results compare with experiment .
.I 181
.W
has any work been done on determining the nature of compressible
viscous flow in a straight channel .
.I 182
.W
in what areas, other than low density wind tunnel flows, is viscous
compressible flow in slender channels a problem .
what analytical investigations have been made of the stability of
conical shells . how do the results compare with experiment .
.I 183
.W
jet interference with supersonic flow  -dash experimental papers .
.I 184
.W
thrust vector control by fluid injection -dash papers .
.I 187
.W
is it possible to obtain a reasonably simple analytical solution to the
heat equation for an exponential (in time) heat input .
.I 189
.W
has anyone programmed a pump design method for a high-speed digital
computer .
.I 190
.W
has anyone derived simplified pump design equation from the fundamental
three-dimensional equations for incompressible nonviscous flow .
.I 196
.W
what are the flutter characteristics of the exposed skin panels of the
x-15 vertical stabilizer when subjected to aerodynamic heating .
.I 200
.W
what agreement is found between theoretically predicted instability
times and experimentally measured collapse times for compressed columns
in creep .
.I 201
.W
theoretical studies of creep buckling .
.I 202
.W
experimental studies of creep buckling .
.I 203
.W
is it possible to correlate the results on the creep buckling of widely
different structures within the framework of a single theory .
.I 204
.W
what are the experimental results for the creep buckling of columns .
.I 205
.W
what are the results for the creep buckling of round tubes under
external pressure .
.I 206
.W
have any analytical studies been conducted on the time-to-failure
mechanism associated with creep collapse for a long circular cylindrical
shell which exhibits both primary and secondary creep as well as elastic
deformations under various distributed force systems .
.I 208
.W
has the effect of initial stresses,  on the frequencies of vibration of
circular cylindrical shells,  been investigated .
.I 209
.W
has the effect of the change of initial pressure due to deformation,  on
the frequencies of vibration of circular cylindrical shells been
investigated .
.I 210
.W
what are the discontinuity stresses at junctions in pressurized
structures .
.I 211
.W
what analytical solutions are available for stresses in edge-loaded
shells of revolution .
.I 212
.W
what dome contours minimize discontinuity stresses when used as closures
on cylindrical pressure vessels .
.I 213
.W
what general solutions for the stresses in pressurized shells of
revolution are available .
.I 214
.W
can studies of pure membrane cylinders having no wall bending stiffness
but maintaining their shape by virtue of internal pressure provide any
insight into the behaviour of pressurized cylinders with finite wall
stiffness .
.I 215
.W
what are the best experimental data and classical small deflection
theory analyses available for pressurized cylinders in bending .
.I 216
.W
does a membrane theory exist by which the behaviour of pressurized
membrane cylinders in bending can be predicted .
.I 217
.W
what are the equations which define the stability of simply supported
corrugated core sandwich cylinders .
.I 218
.W
papers on small deflection theory for buckling of sandwich cylinders .
.I 219
.W
has anyone developed an analysis which accurately establishes the large
deflection behaviour of conical shells .
.I 223
.W
what is the magnitude of second-order wing-body interference
at high supersonic mach number .
.I 224
.W
what is the best theoretical method for calculating pressure on the
surface of a wing alone .
.I 225
.W
how can the effect of the boundary-layer on wing pressure be calculated,
and what is its magnitude .
.I 226
.W
how should the navier-stokes difference equations be solved .
.I 227
.W
which  iterative method for solving linear elliptic
difference equations is most rapidly convergent .
.I 230
.W
technical report on measurement of ablation during flight .
.I 231
.W
what qualitative and quantitative material is available on ablation
materials research .
.I 232
.W
have flow fields been calculated for blunt-nosed bodies and compared
with experiment for a wide range of free stream conditions and body
shapes .
.I 233
.W
what are the available properties of high-temperature air .
.I 234
.W
what is the magnitude of aerodynamic damping in flexible vibration modes
of a slender body of revolution characteristic of launch vehicles .
.I 241
.W
compressive circumferential stresses in a torispherical shell reveal
the possibility of buckling under internal pressure . has anyone
investigated for which ranges of shell parameters these stresses are
sufficiently large to cause elastic buckling .
.I 245
.W
is there an integral method to give a single and sufficiently accurate
method of calculating the laminar separate point for various
incompressible and compressible boundary layers with zero heat transfer .
.I 246
.W
what accurate or exact solutions of the laminar separation point for
various incompressible and compressible boundary layers with zero heat
transfer are available .
.I 247
.W
can the hypersonic similarity results be applied to the technique of
predicting surface pressures of an ogive forebody at angle of attack .
.I 250
.W
what determines the onset of shock-induced boundary-layer separation .
.I 251
.W
are the stable profiles of a compressible boundary layer induced by a
moving wave known .
.I 252
.W
are there experimental results on the stability of a compressible
boundary layer induced by a moving wave .
.I 253
.W
exact solution methods for calculating the ablative mass loss of a
material ablating at high temperatures in a hypersonic flight
environment .
.I 254
.W
what approximate solutions are known to the direct problem of transonic
flow in the throat of a nozzle,  i.e. finding the flow in a given
nozzle .
.I 255
.W
what approximate solutions are known to the indirect problem of
transonic flow in the throat of a nozzle,  i.e. finding a nozzle which
has a given axial velocity distribution .
.I 257
.W
why do users of orthodox pitot-static tubes often find that the
calibrations appear to be,. - (a) significantly different from those formerly
specified,  (b) wildly variable at low reynolds numbers .
.I 259
.W
has a comparison been made between interference-free drag measurements
using free-flight models and similar measurements made in a low-blockage
wind tunnel .
.I 261
.W
solution of the blasius problem with three-point boundary conditions .
.I 264
.W
references on lyapunov's method on the stability of linear
differential equations with periodic coefficients .
.I 265
.W
obtain all papers and reports that contain shock detachment distance
data .
.I 266
.W
work on flow in channels at low reynolds numbers .
.I 267
.W
some approximate analytical heat conduction solutions using methods
other than biot's principle .
.I 268
.W
what mode of stalling can be expected for each stage of an axial
compressor .
.I 269
.W
has a criterion been established for determining the axial compressor
choking line .
.I 272
.W
has a theory of quasi-conical flows been developed, in supersonic
linearised theory, for which the upwash distribution on the lifting
surface, apart from being a homogeneous function in the
co-ordinate, is permitted to have a quite general functional form .
.I 273
.W
how does scale height vary with altitude in an atmosphere .
.I 274
.W
jet interference with supersonic flows
theoretical papers .
.I 275
.W
effects of leading-edge bluntness on the flutter characteristics of some
square-planform double-wedge airfoils at mach numbers less than 15.4.
.I 277
.W
what factors have been shown to have a primary influence on sonic boom
strength .
.I 283
.W
work on small-oscillation re-entry motions .
.I 284
.W
experimental studies on panel flutter .
.I 285
.W
how can wing-body,  flow field interference effects be approximated
rationally .
.I 288
.W
has anyone analytically or experimentally investigated the effects of
internal pressure on the buckling of circular-cylindrical shells under
bending .
.I 291
.W
what theoretical and experimental work has been done on the excitation
and response of typical structures in a noise environment .
.I 292
.W
is there a design method for calculating thermal fatigue endurances of
components of various types and sizes in a variety of circumstances .
.I 293
.W
will an analysis of panel flutter based on arbitrarily assumed modes of
deformation prove satisfactory,  and if so,  what is the minimum number
of modes that need be considered .
.I 294
.W
what is the criterion for true panel flutter,  as opposed to small
amplitude vibration arising from acoustic disturbances .
.I 295
.W
papers dealing with uniformly loaded sectors .
.I 296
.W
general methods of solving clamped plate problems .
.I 297
.W
how can the analytical solution of the buckling strength of a uniform
circular cylinder loaded in axial compression be refined so as to lower
the buckling load .
.I 298
.W
in the problem of the buckling strength of uniform circular cylinders
loaded in axial compression,  does the linear solution help with
improving the non-linear one .
.I 299
.W
the problem of similarity for representative investigation of
aeroelastic effects in a flow with the absence of heating effects .
.I 300
.W
how is fatigue damage estimated using the normal long-hand method .
.I 301
.W
is there any information available on the difference in the effects of
various edge conditions on the buckling of cylindrical shells .
.I 303
.W
have non-linear large deflection analyses been conducted for shell
shapes other than conical .
.I 304
.W
are asymptotic methods sufficiently accurate in the determination of
pre-buckling stresses in torispherical shells,  or must we resort to
numerical methods .
.I 306
.W
what are the nonequilibrium chemical constituents in the viscous shock
layer ahead of a blunt re-entry vehicle .
.I 314
.W
how accurate are existing analytical theories in estimating pressure
distributions on cones at incidence,  at hypersonic speeds .
.I 315
.W
are simple empirical methods of any use for estimating pressure
distribution in cones .
.I 316
.W
do viscous effects seriously modify pressure distributions .
.I 317
.W
has anyone investigated theoretically whether surface flexibility
can stabilize a laminar boundary layer .
.I 321
.W
how do subsonic and transonic flutter data measured in the new langley
transonic dynamics tunnel compare with similar data obtained in other
facilities .
.I 323
.W
how do large changes in new mass ratio quantitatively affect
wing-flutter boundaries .
.I 327
.W
what is the effect of the shape of the drag polar of a lifting
spacecraft on the amount of reduction in maximum deceleration obtainable by
continuously varying the aerodynamic coefficients during re-entry .
.I 331
.W
what are the physical significance and characteristics of separated
laminar and turbulent boundary layer flows .
.I 332
.W
has anyone analytically investigated the stabilizing influence of soft
elastic cores on the buckling strength of cylindrical shells subjected
to non-uniform external pressure .
.I 333
.W
what papers are available on the buckling of empty cylindrical shells
under non-uniform pressure .
.I 335
.W
what effect do thermal stresses have on the compressive buckling
strength of ring-stiffened cylinders .
.I 336
.W
what is the effect on cylinder buckling of a circumferential stress
system that varies in the axial direction .
.I 338
.W
can non-linear shallow shell analysis be reduced to an engineering
technique by use of the matrix .
.I 339
.W
is it possible to predict the shape of a shroud which will allow
simulation of the nose region flow field for a sphere in hypersonic flow .
.I 340
.W
what investigations have been made of the wave system created by a
static pressure distribution over a liquid surface .
.I 347
.W
has anyone investigated the effect of shock generated vorticity on heat
transfer to a blunt body .
.I 348
.W
what is the heat transfer to a blunt body in the absence of vorticity .
.I 349
.W
what are the general effects on flow fields when the reynolds number is
small .
.I 352
.W
find a calculation procedure applicable to all incompressible laminar
boundary layer flow problems having good accuracy and reasonable
computation time .
.I 353
.W
papers applicable to this problem (calculation procedures for laminar
incompressible flow with arbitrary pressure gradient) .
.I 355
.W
has anyone investigated the shear buckling of stiffened plates .
.I 356
.W
papers on shear buckling of unstiffened rectangular plates under shear .
.I 360
.W
in practice, how close to reality are the assumptions that the flow
in a hypersonic shock tube using nitrogen is non-viscous and in
thermodynamic equilibrium .
.I 365
.W
what design factors can be used to control lift-drag ratios at mach
numbers above 5 .