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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data
No Description digital.library.unt.edu/ark:/67531/metadc279644/
The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow
No Description digital.library.unt.edu/ark:/67531/metadc279634/
An experimental study of five annular air inlet configurations at subsonic and transonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc279680/
Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc279650/
Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26
No Description digital.library.unt.edu/ark:/67531/metadc279664/
A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel
No Description digital.library.unt.edu/ark:/67531/metadc279629/
Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model
No Description digital.library.unt.edu/ark:/67531/metadc57810/
The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage
No Description digital.library.unt.edu/ark:/67531/metadc57818/
Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms
No Description digital.library.unt.edu/ark:/67531/metadc57814/
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness
No Description digital.library.unt.edu/ark:/67531/metadc57819/
An analytical method of estimating turbine performance
A method is developed by which the performance of a turbine over a range of operating conditions can be analytically estimated from the blade angles and flow areas. In order to use the method, certain coefficients that determine the weight flow and friction losses must be approximated. The method is used to calculate the performance of the single-stage turbine of a commercial aircraft gas-turbine engine and the calculated performance is compared with the performance indicated by experimental data. For the turbine of the typical example, the assumed pressure losses and turning angles give a calculated performance that represents the trends of the experimental performance with reasonable accuracy. The exact agreement between analytical performance and experimental performance is contingent upon the proper selection of the blading-loss parameter. A variation of blading-loss parameter from 0.3 to 0.5 includes most of the experimental data from the turbine investigated. digital.library.unt.edu/ark:/67531/metadc57971/
The subsonic aerodynamic characteristics of two double-wedge airfoil sections suitable for supersonic flight
No Description digital.library.unt.edu/ark:/67531/metadc57977/
Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61
No Description digital.library.unt.edu/ark:/67531/metadc57970/
: The linear perturbation theory of axially symmetric compressible flow with application to the effect of compressibility on the pressure coefficient at the surface of a body of revolution
No Description digital.library.unt.edu/ark:/67531/metadc57978/
Aerodynamic characteristics of flying-boat hulls having length-beam ratios of 20 and 30
No Description digital.library.unt.edu/ark:/67531/metadc57974/
Theoretical investigation of the dynamic lateral stability characteristics of Douglas design No. 39C, an early version of the X-3 research airplane
Contains results of calculations made to determine the neutral oscillatory stability boundaries, period and time to damp of the oscillatory mode, and motions following disturbances. The calculations were made for Mach numbers of 0.75 and 2.3 at an attitude of 35,000 feet and for the landing condition at sea level. digital.library.unt.edu/ark:/67531/metadc57979/
Lateral-control investigation on a 37 degree sweptback wing of aspect ratio 6 at a Reynolds number of 6,800,000
No Description digital.library.unt.edu/ark:/67531/metadc57976/
Experimental investigation of the effects of support interference on the drag of bodies of revolution at a Mach number of 1.5
No Description digital.library.unt.edu/ark:/67531/metadc57973/
A study of several parameters controlling the trajectories of a supersonic antiaircraft missile powered with solid- or liquid-fuel rockets
No Description digital.library.unt.edu/ark:/67531/metadc57965/
Drag measurements in flight on the 10-percent-thick and 8-percent-thick wing X-1 airplanes
No Description digital.library.unt.edu/ark:/67531/metadc57962/
Calculation of aerodynamic forces on a propeller in pitch or yaw
No Description digital.library.unt.edu/ark:/67531/metadc57961/
Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 I : maximum thickness at 20 percent of the chord
No Description digital.library.unt.edu/ark:/67531/metadc57967/
Longitudinal stability and control characteristics of a semispan airplane model at transonic speeds as obtained by the transonic-bump method
No Description digital.library.unt.edu/ark:/67531/metadc57960/
Effect of aerodynamic hysteresis on critical flutter speed at stall
No Description digital.library.unt.edu/ark:/67531/metadc57968/
Experimental study of loop-scavenged compression-ignition cylinder for gas-generator use
No Description digital.library.unt.edu/ark:/67531/metadc57964/
Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92
No Description digital.library.unt.edu/ark:/67531/metadc57969/
Lateral and directional stability and control characteristics of a C-54D airplane
Data are presented showing compliance of C-54D with Army and Navy lateral and directional stability and control specifications. The airplane met requirements except for the rolling effectiveness pb/2V, the aileron forces in rolling, and the rudder forces in the asymmetric power conditions which were marginal. Also, the results of special tests concerning asymmetric power, asymmetric loading, and pitch due to yaw requested by the Airplane Handling Qualities Subcommittee of the Air Transport Association are presented. digital.library.unt.edu/ark:/67531/metadc57966/
An investigation of aileron oscillations at transonic speeds on NACA 23012 and NACA 65-212 airfoils by the wing-flow method
An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably well with full-scale flight results. digital.library.unt.edu/ark:/67531/metadc57963/
Effect of centrifugal force on critical flutter speed on a uniform cantilever beam
Semirigid flutter theory is used. Calculations are made on airfoils with fundamental bending frequencies up to 2000 radian per second. Centrifugal force can under certain conditions reduce the critical flutter speed. digital.library.unt.edu/ark:/67531/metadc57975/
NACA investigation of fuels corresponding to specification AN-F-58 : results of studies in single combustors of J-33, J-34, J-35, and NENE turbojet engines
No Description digital.library.unt.edu/ark:/67531/metadc57972/
Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel II : the effectiveness and hinge moments of a constant-chord plain flap
No Description digital.library.unt.edu/ark:/67531/metadc57740/
Investigation of flow conditions and the nature of the wall-constriction effect near and at choking by means of the hydraulic analogy
No Description digital.library.unt.edu/ark:/67531/metadc57744/
Performance of several air ejectors with conical mixing sections and small secondary flow rates
No Description digital.library.unt.edu/ark:/67531/metadc57745/
Wind-tunnel tests of a swept-blade propeller and related straight blades having thickness ratios of 5 and 6 percent
No Description digital.library.unt.edu/ark:/67531/metadc57742/
Internal-Film Cooling of Rocket Nozzles
Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous ring of 3.5 percent of propellant flow stabilized wall temperature in convergent section but did not adequately cool throat or divergent sections. digital.library.unt.edu/ark:/67531/metadc57642/
Ice protection of turbojet engines by inertia separation of water III : annular submerged inlets
Aerodynamic and icing studies were conducted on a one-half-scale model of an annular submerged inlet for use with axial-flow turbojet engines. Pressure recoveries, screen radial-velocity profiles, circumferential mass-flow variations, and icing characteristics were determined at the compressor inlet. In order to be effective in maintaining water-free induction air, the inlet gap must be extremely small and ram-pressure recoveries consequently are low, the highest achieved being 65 percent at inlet-velocity ratio of 0.86. All inlets exhibited considerable screen icing. Severe mass-flow shifts occurred at angles of attack. digital.library.unt.edu/ark:/67531/metadc57641/
Limited measurements of static longitudinal stability in flight of Douglas D-558-1 airplane (BuAero No. 37971)
Contains a few measurements of the variation of elevator angle and elevator force with Mach number at 30,000 feet altitude up to a Mach number of 0.85. These data show that the airplane possessed positive static longitudinal stability up to a Mach number of 0.80. A trim change in the nose-down direction occurred for Mach numbers above 0.82. digital.library.unt.edu/ark:/67531/metadc57647/
Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen
Theoretical performance data including nozzle-exit temperature, specific impulse, volume specific impulse and composition, temperature, and mean molecular weight of reaction products based on frozen equilibrium and isentropic expansion are presented for 13 propellant combinations at reaction pressure of 300 pounds per square inch absolute and expansion ratio of 20.4. On basis of maximum specific impulse alone, five fuels had the following order for any given oxidant: liquid hydrogen, hydrazine, liquid ammonia, and either hydrazine hydrate or hydroxylamine. Three oxidants with a given fuel had the following order: liquid ozone, liquid oxygen, and 100-percent hydrogen peroxide. digital.library.unt.edu/ark:/67531/metadc57648/
Preliminary investigation of combustion in flowing gas with various turbulence promoters
No Description digital.library.unt.edu/ark:/67531/metadc57665/
Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25
Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics. digital.library.unt.edu/ark:/67531/metadc57662/
Flight tests of a two-dimensional wedge diffuser at transonic and supersonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc57660/
Investigation of horn balances on a 45 degree sweptback horizontal tail surface at high subsonic speeds
A wind-tunnel investigation of horn balances on a 45 degree sweptback, semispan, horizontal tail surface was made to determine the effects of horn size and inboard-edge fairing at a Mach number of 0.30 and to determine the effects of compressibility up to a Mach number of 0.89. Presented are lift, drag, pitching-moment, and hinge-moment data and lift and hinge-moment parameters. digital.library.unt.edu/ark:/67531/metadc57828/
Vibration survey of blades in 10-stage axial-flow compressor I : static investigation
No Description digital.library.unt.edu/ark:/67531/metadc57824/
Langley free-flight-tunnel investigation of the automatic lateral stability characteristics of a model equipped with a gyro stabilizing unit that provided either flicker-type or hunting control
No Description digital.library.unt.edu/ark:/67531/metadc57826/
Residual stress analysis of overspeeded disk with central hole by x-ray diffraction
An X-ray - diffraction analysis of residual surface stresses after plastic strain was introduced in a parallel-sided 3S-O aluminum disk with a central hole by two types of centrifugal overspeed is reported. Both tangential and radial stresses were generally tensile with large local variations near the hole where surface stresses may have been partly superficial. These stresses were both tensile and compressive dependent on the distance from the disk center when mass compression was effected near the hole. digital.library.unt.edu/ark:/67531/metadc57823/
Some flight measurements of pressure-distribution and boundary-layer characteristics in the presence of shock
No Description digital.library.unt.edu/ark:/67531/metadc57592/
An exploratory investigation of the relative merits of split and chord-extension flaps on a 45 degrees swept-back wing
No Description digital.library.unt.edu/ark:/67531/metadc57591/
Some effects of gutter flame-holder dimensions on combustion-chamber performance of 20-inch ram jet
No Description digital.library.unt.edu/ark:/67531/metadc57590/
The effects of high-lift devices on the low-speed stability of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow
Contains results of tunnel tests to determine effects of various combinations of split flaps, slats, and nose slats on the stability characteristics of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow. digital.library.unt.edu/ark:/67531/metadc57946/
An evaluation of air-borne radar as a means of avoiding atmospheric turbulence
No Description digital.library.unt.edu/ark:/67531/metadc57943/
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