# 分类:1958

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1958 年论文列表

## 分类“1958”中的页面

以下167个页面属于本分类，共167个页面。

### A

- A Comparative Analysis of the Performance of Long-Range Hypervelocity Vehicles
- A correlation of results of flight investigation with results of an analytical study of effects of wing flexibility on wing strains due to gusts
- A Flight Evaluation of the Factors which Influence the Selection of Landing Approach Speeds
- A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition
- A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition
- A method for simulating the atmospheric entry of long-range ballistic missiles
- A method of computing the transient temperature of thick walls from arbitrary variation of adiabatic-wall temperature and heat-transfer coefficient
- A phenomenological relation between stress, strain rate, and temperature for metals at elevated temperatures
- A simplified method for approximating the transient motion in angles of attack and sideslip during a constant rolling maneuver
- A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds
- A Summary of Preliminary Investigations into the Characteristics of Combustion Screech in Ducted Burners
- A Theoretical and Experimental Study of Planing Surfaces Including Effects of Cross Section and Plan Form
- A Three-Dimensional Flow Expander as a Device to Increase the Mach Number in a Supersonic Wind Tunnel
- A variational theorem for creep with applications to plates and columns
- A Wind-Tunnel Investigation of the Aerodynamic Characteristics of a Full-Scale Supersonic-Type Three-blade Propeller at Mach Numbers to 0.96
- Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls
- Aerodynamic Characteristics in Sideslip of a Large-Scale 49 deg Sweptback Wing-Body-Tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge
- Aerodynamic performance and static stability and control of flat-top hypersonic gliders at Mach numbers from 0.6 to 18
- Aerodynamic Research on Fuselages with Rectangular Cross Section
- Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6
- An acceleration schedule control for accelerating a turbojet engine and its use with a speed control
- An analog computer study of the effectiveness of interceptor commands derived from a prediction equation of second order
- An experimental investigation of sting-support effects on drag and a comparison with jet effects at transonic speeds
- An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers from 3.0 to 6.3
- An investigation of supersonic store interference in the vicinity of a 22 deg swept wing fuselage configuration at Mach numbers of 1.61 and 2.01
- An Investigation of the Drag Characteristics of a Tailless Delta-Wing Airplane in Flight, Including Comparison with Wind-Tunnel Data
- An Investigation of the Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane with Alternate Nose Configurations with and without Wing Fuel Tanks, TED No. NACA AD 395
- Analysis of Flight-determined and Predicted Effects of Flexibility on the Steady-state Wing Loads of the B-52 Airplane
- Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01
- Analytical and Experimental Determination of the Coupled Natural Frequencies and Mode Shapes of a Dynamic Model of a Single-Rotor Helicopter
- Application of the Method of Coordinate Perturbation to Unsteady Duct Flow
- Approximate analysis of effects of large deflections and initial twist on torsional stiffness of a cantilever plate subjected to thermal stresses
- Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll
- Area-Suction Boundary-Layer Control as Applied to the Trailing-Edge Flaps of a 35 Degree Swept-Wing Airplane

### B

- Basic Pressure Measurements at Transonic Speeds on a Thin 45 deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations
- Blowing-Type Boundary-Layer Control as Applied to the Trailing-Edge Flaps of a 35 Degree Swept-Wing Airplane
- Boron and Zirconium from Crucible Refractories in a Complex Heat-Resistant Alloy
- Boundary-Layer-Transition Measurements in Full-Scale Flight
- BUFFET TESTS OF AN ATTACK-AIRPLANE MODEL WITH EMPHASIS ON ANALYSIS OF DATA FROM WIND-TUNNEL TESTS

### C

- Calculated and measured stresses in simple panels subject to intense random acoustic loading including the near noise field of a turbojet engine
- Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data
- Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers from 0.94 to 2.58
- Characteristics of the Langley 8-foot Transonic Tunnel with Slotted Test Section
- Combustion of gaseous hydrogen at low pressures in a 35 deg sector of a 28-inch-diameter ramjet combustor
- Compressible Laminar Boundary Layer over a Yawed Infinite Cylinder with Heat Transfer and Arbitrary Prandtl Number

### D

- DESIGN AND EXPERIMENTAL INVESTIGATION OF A SINGLE-STAGE TURBINE WITH A ROTOR ENTERING RELATIVE MACH NUMBER OF 2
- Differential equations of motion for combined flapwise bending, chordwise bending, and torsion of twisted nonuniform rotor blades
- Ditching Investigations of Dynamic Models and Effects of Design Parameters on Ditching Characteristics
- Drag Minimization for Wings and Bodies in Supersonic Flow

### E

- Effect of Chord Size on Weight and Cooling Characteristics of Air-Cooled Turbine Blades
- Effect of Fuel Variables on Carbon Formation in Turbojet-Engine Combustors
- Effect of Nose Length, Fuselage Length, and Nose Fineness Ratio on the Longitudinal Aerodynamic Characteristics of Two Complete Models at High Subsonic Speeds
- EFFECT OF PRESSURE LEVEL ON AFTERBURNER-WALL TEMPERATURES
- Effect of Rest Periods on Fatigue of High-Purity Aluminum
- Effect of Several Afterbody Modifications Including Terminal Fairings on the Drag of a Single-engine Fighter Model with Hot-jet Exhaust
- Effect of Target Thickness on Cratering and Penetration of Projectiles Impacting at Velocities to 13,000 Feet Per Second
- Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-tail Component Drag of a Twin-engine Fighter-type Airplane Model
- Effects of Body Shape on the Drag of a 45 degree Sweptback-Wing-Body Configuration at Mach Numbers from 0.90 to 1.43
- Effects of modifications to a control surface on a 6-percent-thick unswept wing on the transonic control-surface flutter derivatives
- Effects of Yaw on the Heat Transfer to a Blunt Cone-Cylinder Configuration at a Mach Number of 1.98
- Elliptic Cones Alone and with Wings at Supersonic Speed
- Elliptic Functions and Integrals with Real Modulus in Fluid Mechanics
- Estimation of Directional Stability Derivatives at Small Angles and Subsonic and Supersonic Speeds
- Evaporation, Heat Transfer, and Velocity Distribution in Two-Dimensional and Rotationally Symmetrical Laminar Boundary-Layer Flow
- Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Deg Swept- Wing-Fuselage Configuration at a Mach Number of 1.61
- Experimental Behavior of Pentaborane-Air Combustion Products During Expansion in a Convergent Divergent Nozzle
- Experimental Determination of Effects of Frequency and Amplitude on the Lateral Stability Derivatives for a Delta, a Swept, and Unswept Wing Oscillating in Yaw
- Experimental investigation of a high subsonic mach number turbine having a 40-blade rotor with zero suction-surface diffusion
- Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile
- Experimental Wind-Tunnel Investigation of the Transonic Damping-in-Pitch Characteristics of Two Wing-Body Combinations
- Extreme Speeds and Thermodynamic States in Supersonic Flight

### F

- Flight Investigation of a Normal-Acceleration Automatic Longitudinal Control System in a Fighter Airplane
- Flight Measurements of Some of the Flying Qualities and Stability Derivatives of a Supersonic Fighter Airplane
- Free Convection Under the Conditions of the Internal Problem
- Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10
- Free-flight investigation of the drag of a 60 deg delta-wing configuration with large stores mounted below the indented fuselage at mach numbers between 0.8 and 1.6
- Free-Spinning-Tunnel Investigation of a 1/17 Scale Model of the Cessna T-37A Airplane
- Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112
- Full-Scale Investigation of Several Jet-Engine Noise-Reduction Nozzles

### G

### H

- Heat Transfer in the Turbulent Incompressible Boundary Layer. 3; Arbitrary Wall Temperature and Heat Flux
- Heat Transfer in the Turbulent Incompressible Boundary Layer. Part 1; Constant Wall Temperature
- Heat Transfer in the Turbulent Incompressible Boundary Layer. Part 2; Step Wall-Temperature Distribution
- Heat Transfer Measured in Free Flight on a Slightly Blunted 25 deg Cone-Cylinder-Flare Configuration at Mach Numbers up to 9.89
- Heat-Transfer and Friction Measurements with Variable Properties for Airflow Normal to Finned and Unfinned Tube Banks
- Heat-Transfer and Pressure Measurements from a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power
- Heat-Transfer and Pressure Measurements from a Flight Test of the Third 1/18-Scale Model of the Titan Intercontinental Ballistic Missile up to a Mach Number of 3.86 and Reynolds Number per Foot of 23.5 x 10(exp 6) and a Comparison with Heat Transfer
- Heat-Transfer Measurements on a 5.5- Inch-Diameter Hemispherical Concave Nose in Free Flight at Mach Numbers up to 6.6
- High mach number, low-cowl-drag, external- compression inlet with subsonic dump diffuser
- Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

### I

- Impact on a Compressible Fluid
- Inclined Bodies of Various Cross Sections at Supersonic Speeds
- Incompressible flutter characteristics of representative aircraft wings
- Induction System Characteristics and Engine Surge Occurrence for Two Fighter-type Airplanes
- Investigation of a Nonlinear Control System
- Investigation of a Prototype Iroquois Turbojet Engine in an Altitude Test Chamber. COORD. NO. AF-P-6
- Investigation of aerodynamic characteristics of an airplane configuration having tail surfaces outboard of the wing tips at Mach numbers of 2.30, 2.97, and 3.51
- Investigation of an all-movable control surface at a mach number of 6.86 for possible flutter
- Investigation of Aperiodic Time Processes with Autocorrelation and Fourier Analysis
- Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile with Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51
- Investigation of Incipient Spin Characteristics of a 1/35-Scale Model of the Convair F-102A Airplane, Coord. No. AF-AM-79
- Investigation of Inlet Control Parameters for an External-internal-compression Inlet from Mach 2.1 to 3.0
- Investigation of lithium hydride and magnesium as high-temperature internal coolants with several skin materials
- Investigation of Separated Flows in Supersonic and Subsonic Streams with Emphasis on the Effect of Transition
- Investigation of Some Wake Vortex Characteristics of an Inclined Ogive-Cylinder Body at Mach Number 2
- Investigation of the Drag of Various Axially Symmetric Nose Shapes of Fineness Ratio 3 for Mach Numbers from 1.24 to 7.4
- Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

### L

- Large-Scale Wind-Tunnel Tests of an Airplane Model with an Unswept, Aspect-Ratio-10 Wing, Two Propellers, and Blowing Flaps
- Lift, Drag, and Pitching Moment of an Aspect-Ratio-2 Triangular Wing with Leading-Edge Flaps Designed to Simulate Conical Camber
- Line following servosystem Patent
- Longitudinal and Lateral Stability and Control Characteristics and Vertical-Tail-Load Measurements for a 0.03-Scale Model of the Avro CF-105 Airplane at Mach Numbers of 1.60, 1.80, and 2.00
- Longitudinal and Lateral Stability and Control Characteristics of Various Combinations of the Component Parts of Two Canard Airplane Configurations at Mach Numbers of 1.41 and 2.01
- Low-Speed Aerodynamic and Hydrodynamic Characteristics of a Proposed Supersonic Multijet Water-Based Hydro-Ski Aircraft with Upward-Rotating Engines
- Low-Speed Static Stability Characteristics of Two Configurations Suitable for Lifting Reentry from Satellite Orbit

### M

### N

### O

- On flow of electrically conducting fluids over a flat plate in the presence of a transverse magnetic field
- On Possible Similarity Solutions for Three-Dimensional Incompressible Laminar Boundary-Layer Flows Over Developable Surfaces and with Proportional Mainstream Velocity Components
- On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas
- Origin and Prevention of Crash Fires in Turbojet Aircraft

### P

- Performance of a 28-inch ramjet utilizing gaseous hydrogen at a mach number of 3.6, angles of attack up to 12 deg, and pressure altitudes up to 110,000 feet
- Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50
- Performance of JP-4 fuel with fluorine- oxygen mixtures in 1000-pound-thrust rocket engines
- Performance of multiple jet-exit installations
- Preliminary aerodynamic data pertinent to manned satellite reentry configurations
- Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane
- Preliminary transonic performance results for solid and slotted turbojet nacelle afterbodies incorporating fixed divergent jet nozzles designed for supersonic operation

### S

- Some Altitude Operational Characteristics of a Prototype Iroquois Turbojet Engine. COORD. NO. AF-P-6
- Some effects of flow spoilers and of aerodynamic balance on the oscillating hinge moments for a swept fin-rudder combination in a transonic wind tunnel
- Some Effects of Horizontal-Tail Position on the Vertical-Tail Pressure Distributions of a Complete Model in Sideslip at High Subsonic Speeds
- Some Effects of Rapid Inlet Pressure Oscillation on the Operation of a Turbojet Engine
- Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30 Deg Blunted Nose Cone
- Stability of Cylindrical and Conical Shells of Circular Cross Section, with Simultaneous Action of Axial Compression and External Normal Pressure
- Static Investigation of Paddle Vane Oscillating in Jet of 1,300-Pound-Thrust Rocket Motor
- Statistical Study of Turbulence: Spectral Functions and Correlation Coefficients
- Structural Design and Preliminary Evaluation of a Lightweight, Brazed, Air-Cooled Turbine Rotor Assembly
- Supersonic Wave Interference Affecting Stability
- Survey of Hydrogen Combustion Properties
- Systematic Two-Dimensional Cascade Tests of NACA 65-Series Compressor Blades at Low Speeds

### T

- The Effects of Longitudinal Control-System Dynamics on Pilot Opinion and Response Characteristics as Determined from Flight Tests and from Ground Simulator Studies
- The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube
- The mechanism of thermal-gradient mass transfer in the sodium hydroxide-nickel system
- The response of an airplane to random atmospheric disturbances
- The similarity rules for second-order subsonic and supersonic flow
- The Thermal Stability of Unsymmetrical Dimethylhydrazine
- The Turbulent Boundary Layer on a Rough Curvilinear Surface
- Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas
- Theoretical Combustion Performance of Several High-Energy Fuels for Ramjet Engines
- Theory of self-excited mechanical oscillations of helicopter rotors with hinged blades
- Thin airfoil theory based on approximate solution of the transonic flow equation
- Three-Dimensional Orbits of Earth Satellites, Including Effects of Earth Oblateness and Atmospheric Rotation
- Transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane
- Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
- Transonic-Wind-Tunnel Tests of the Aerodynamic Characteristics of a 0.15-Scale Model of the North American Aviation 255-Inch Fin-Stabilized External Store, Coord No. AF-AM-4
- Turbine Engines for High-Speed Flight
- Turbulent Heat-Transfer Coefficients in the Vicinity of Surface Protuberances
- Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers

### U

- Use of highly reactive chemical additives to improve afterburner performance at altitude
- Use of stage-stacking technique for predict- ing over-all performance in multistage axial- flow compressor utilizing interstage-air bleed
- Use of the Kernel function in a three-dimensional flutter analysis with application to a flutter-tested delta-wing model

### W

- Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls
- Wind-Tunnel Investigation of Some Effects of Wing Sweep and Horizontal-Tail Height on the Static Stability of an Airplane Model at Transonic Speeds
- Wind-Tunnel Investigation of the Low-Speed Characteristics of a 1/8-Scale Model of the Republic XP-91 Airplane with a Vee and a Conventional Tail. Addendum - Characteristics with a Revised Conventional Tail and Drooped Wing Tips