National Advisory Committee for Aeronautics (NACA) - 208 Matching Results
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- Simulator studies of a simple homing system
- Report presenting simulator studies of a homing missile pursuing a constant-velocity nonmaneuvering target. The missile dynamics in pitch and roll, seeker method of deflection and control, and the missile-target geometry were simulated to determine whether the method of control and detection in conjunction with the missile dynamics were feasible.
- Free-flight investigation to obtain drag-at-lift and stability data for a 60 degree delta-wing-body configuration over a Mach number range of 1.3 to 1.6
- Report presenting flight tests using a rocket-propelled 60 degree delta-wing body configuration, which included a NACA 0003-63 wing airfoil section. Drag at lift and stability data were obtained for a range of Mach numbers.
- Static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile at Mach numbers of 1.41, 1.61, and 2.01: TED No. NACA AD 398
- Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile. The tests were made at three Mach and Reynolds numbers.
- Lift and drag characteristics of the Douglas X-3 research airplane obtained during demonstration flights to a Mach number of 1.20
- Report presenting lift and drag data obtained during the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift. A comparison of the flight data with data from wind-tunnel and rocket-model tests shows that the model tests adequately predict the performance of the airplane.
- Investigation of a 10-stage subsonic axial-flow research compressor 4: performance evaluation and flow distributions in the first, fifth, and tenth stages
- Report presenting a determination of the performance and flow distributions in the first, fifth, and tenth stages of a 10-stage axial-flow research compressor at design and part speed in order to study the validity of the compressor design assumptions and to show the effects of part-speed compressor operation on stage performance.
- An Investigation of the Adaptation of a Transonic Slotted Tunnel to Supersonic Operation by Enclosing the Slots With Fairings
- Memorandum presenting an experimental investigation of the adaptation of a transonic slotted tunnel to supersonic operation by enclosing the slots with fairings. The adaptation allows the extension of peak Mach number of the tunnel to be made at a reasonable cost in both time and effort, provided simplicity and ease of installation are taken into consideration during the design of the cover fairings. The nozzle is found to be sensitive to phenomena that will cause thickening of the boundary layer in the slot cover fairing.
- Preliminary results of natural icing of an axial-flow turbojet engine
- Report presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Results regarding the tail-pipe temperature, engine jet thrust, and characteristics of ice formation are provided. No general conclusions can be reached from the data because the icing condition was relatively light.
- Charts for Determining Preliminary Values of Span-Load, Shear, Bending-Moment, and Accumulated-Torque Distributions of Swept Wings of Various Taper Ratios
- Contains charts for use in determining preliminary values of the spanwise-load, shear, bending-moment, and accumulated-torque distributions of swept wings. The charts are based on strip theory and include four aerodynamic-load distributions, two section-moment distributions, and two inertia-load distributions. The taper ratios considered cover the range from 1.0 to 0 and the results are applicable to any angle of sweep.
- Initial Experiments on Flutter of Unswept Cantilever Wings at Mach Number 1.3
- Report presenting the results of a preliminary experimental flutter investigation of widely different unswept cantilever wings at Mach number 1.3. Wings with a variety of mass-density parameters, center-of-gravity positions, and elastic-axis positions were tested.
- The effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing
- "An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces" (p .1).
- 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.
- Experimental Investigation of the Effects of Vortex Generators on the Maximum Lift of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Section
- Report discussing testing in the low-turbulence tunnel to determine the effectiveness of several configurations of vortex generators in increasing maximum lift of a 6-percent-thick symmetrical circular-arc airfoil section. None of the configurations tested were found to greatly increase the lift. Some of the configurations tested included a single row of vortex generators, two rows of generators, larger vortex generators, and sweeping forward the front row of generators.
- Rocket-Model Investigation to Determine the Force and Hinge-Moment Characteristics of a Half-Delta Tip Control on a 59 Degree Sweptback Delta Wing Between Mach Numbers of 0.55 and 1.43
- Report presenting a free-flight investigation of a rocket-powered control research model to determine the force and hinge-moment characteristics of a half-delta tip control on a delta wing. Results regarding the control hinge moments, control normal force, and total normal force are provided.
- Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 3.67
- Report presenting foredrag measurements made at zero angle of attack for a series of fineness ratio 3 nose shapes. The types of noses investigated included theoretically derived minimum drag shapes, hemispherically blunted cones, and other more common profiles. Results regarding hemispherically blunted cones, theoretical minimum drag nose shapes, and comparison of foredrag of all the force models are provided.
- Effect of fuel properties on carbon deposition in atomizing and prevaporizing turbojet combustors
- Report presenting investigations of the effects of fuel properties on combustion-chamber carbon deposition in singe tubular fuel-atomizing and fuel-prevaporizing combustors. The NACA K factor and the smoking tendency were approximately equally effective in relating carbon-deposition data from the prevaporizing and atomizing combustors. Results regarding the K factor, smoking tendency, effect of prevaporizing combustor operating conditions, sulfur, gum, and olefin, are provided.
- Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques
- Report discussing the results of an investigation to determine the stability and control characteristics of a flying model of an unswept-wing vertically rising airplane. Information about stabilization, maneuverability, rolling motions, and landings is provided.
- Wind-Tunnel Investigation at Low Speed of the Effects of Symmetrical Deflection of Half-Delta Tip Controls on the Damping in Roll and Yawing Moment Due to Rolling of a Triangular-Wing Model
- Report presenting a low-speed investigation in the stability tunnel to determine the effects of symmetrical deflection of half-delta tip controls on the damping in roll and yawing moment due to rolling of a model with triangular wings. Triangular wings have numerous aerodynamic advantages, but it is difficult to obtain adequate longitudinal and lateral control with acceptable control forces when using them. Results regarding the lift characteristics and rolling characteristics are provided.
- Experimental investigation of axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers 2: blade-coordinate data
- "Supplementary blade-design data including rotor- and stator-blade coordinates and mean-line angles at the leading and the trailing edges are presented for a transonic axial-flow compressor inlet stage" (p. 1).
- Low-speed wind-tunnel investigation of a thin 60 degree delta wing with double slotted, single slotted, plain, and split flaps
- Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a thin delta wing equipped with various arrangements of double slotted, single slotted, plain, and split flaps. The wing was a flat plate with beveled leading and trailing edges and had a maximum thickness ratio of 0.045, and 60 degrees sweepback of the leading edge.
- Altitude Wind Tunnel Investigation of the Prototype J40-WE-8 Turbojet Engine Without Afterburner
- From Introduction: "As part of a comprehensive investigation of the J40 turbojet engine conducted at the NACA Lewis altitude wind tunnel, the steady-state engine performance of the prototype J40-WE-8 turbojet engine without afterburner was obtained and is presented herein. A basic redesign of the compressor and other modifications in the compressor and the combustor were incorporated in the XJ40-WE-6 turbojet engine (references 2 and 3). In this report the modified engine is designated "the prototype J40-WE-8 without afterburner."
- Preliminary Tank Tests of Some Hydro-Ski-Wheel Combinations in the Planing Condition
- Report presenting an investigation of the planing characteristics of various combinations of a wheel and a hydro-ski. Models tested included at least two values of the following parameters: diameter of wheel, width of wheel, cross-section shape of wheel, fore-and-aft location of wheel, lateral location of wheel, gap between wheel and ski, rotation of wheel, and protrusion of wheel. Results regarding the general effect of a wheel, effect of wheel shape and size, effect of wheel-ski arrangement, and possible methods of reducing resistance are provided.
- A preliminary gust-tunnel investigation of leading-edge separation on swept wings
- Report presenting the results of a series of qualitative studies with tufts on three wings with sweepback angles of 30 degrees, 45 degrees, and 60 degrees, which show that under certain conditions, a leading-edge vortex can exist in the unsteady flow associated with a gust. The results indicated that if a wing in steady flight prior to entering a gust is at an angle of attack several degrees less than that at which vortex flow first begins in steady flow, it may penetrate the gust without having the vortex develop, even if its angle of attack is increased by the gust into the vortex-flow regime.
- Altitude performance investigation of two flame-holder and fuel-system configurations in short afterburner
- From Introduction: "The results of this complete evaluation of the altitude performance and operational characteristics of the two types of flame-holder and fuel-system configurations are reported herein.The starting limits of both configurations at a flight Mach number of 0.6 are also discussed."
- Effect of Fuel-Air Distribution on Performance of a 16-Inch Ram-Jet Engine
- Report presenting an investigation of the effect of combustion on diffusion in the fuel preparation zone of a ram-jet engine. The information was applied in the design of combustor to operate at lean fuel-air ratios.
- Experimental Investigation of Internal Flow Characteristics of Forward Underslung Fuselage Scoops With Unswept Entrances at Mach Numbers of 1.41 to 1.96
- Report presenting an investigation of two versions of a type of forward underslung scoop mounted on a pointed fuselage in the supersonic blowdown tunnel. The scoop entrances were in the shape of a 60 degree sector of an annulus, but the sides of one scoop were sweptback, while the others were unswept. Results regarding the shadowgraphs and surface-pressure distributions and total-pressure recovery are provided.
- Study of the physical properties of petrolatum-stabilized magnesium-hydrocarbon slurry fuels
- Magnesium-hydrocarbon slurries containing a moderate proportion of petrolatum have physical properties such that they offer promise as experimental aircraft fuels. The settling of the magnesium is greatly retarded by the petrolatum, and the slurries can easily be remixed to their original condition after storage. Successive batches which have closely similar properties can be prepared readily. The apparent viscosity of these slurries increased rapidly with increasing magnesium concentration, with increasing petrolatum concentration, and with decreasing temperature. As the apparent viscosity increased, the extent of settling and the ease of remixing both decreased. Although no quantitative correlation was found between the properties of the slurry and those of the petrolatum, and no one petrolatum gave slurries which were best in all respects, one of the five petrolatum used was judged to be superior to the others.
- Preliminary investigation of performance and starting characteristics of liquid fluorine: Liquid oxygen mixtures with jet fuel
- From Summary: "The performance of jet fuel with an oxidant mixture containing 70 percent liquid fluorine and 30 percent liquid oxygen by weight was investigated in a 500-pound-thrust engine operating at a chamber pressure of 300 pounds per square inch absolute. A one-oxidant-on-one-fuel skewed-hole impinging-jet injector was evaluated in a chamber of characteristic length equal to 50 inches. A maximum experimental specific impulse of 268 pound-seconds per pound was obtained at 25 percent fuel, which corresponds to 96 percent of the maximum theoretical specific impulse based on frozen composition expansion."
- Transonic Flight Tests to Compare the Zero-Lift Drags of 45 Degree Sweptback Wings of Aspect Ratio 3.55 and 6.0 With and Without Nacelles at the Wing Tips
- Report presenting tests of rocket-propelled models at transonic speeds to compare the zero-lift drags of 45 degree sweptback wings with and without solid nacelles at the wing tips. The wing drag coefficient was lowered at high subsonic and supersonic speeds when the aspect ratio was reduced from 6.0 to 3.55. Results regarding the favorability of the wing-tip nacelles and the force-break Mach number of the varying configurations are also provided.
- Pressure Pulsations on Rigid Airfoils at Transonic Speeds
- Report presenting testing to obtain the effects of changes in Mach number, thickness ratio, and angle of attack on the amplitude of the pressure pulsations on several airfoils at transonic speeds. The tests were performed on NACA 65A-series airfoils with thicknesses ranging from 4 to 12 percent chord at a range of Mach numbers and angles of attack. The relations of pressure pulsations to buffeting are also provided.
- Performance and operational characteristics of a python turbine-propeller engine at simulated altitude conditions
- "The performance and operational characteristics of a Python turbine-propeller engine were investigated at simulated altitude conditions in the NACA Lewis altitude wind tunnel. In the performance phase, data were obtained over a range of engine speeds and exhaust nozzle areas at altitudes from 10,000 to 40,000 feet at a single cowl-inlet ram pressure ratio; independent control of engine speed and fuel flow was used to obtain a range of powers at each engine speed. Engine performance data obtained at a given altitude could not be used to predict performance accurately at other altitudes by use of the standard air pressure and temperature generalizing factors" (p. 1).
- Performance of single-stage compressor designed on basis of constant total enthalpy with symmetrical velocity diagram at all radii and velocity ratio of 0.7 at rotor hub
- A typical inlet axial-flow compressor inlet stage, which was designed on the basis of constant total enthalpy with symmetrical velocity diagram at all radii, was investigated. At a tip speed of 1126 feet per second, a peak pressure ratio of 1.28 was obtained at an efficiency of 0.76. At a tip speed, the highest practical flow was 28 pounds per second per square foot frontal area with an efficiency of 0.78. Data for a rotor relative inlet Mach number range of from 0.5 to 0.875 indicates that the critical value for any stage radial element is approximately 0.80 for the stage investigated.
- Preliminary investigation of the heat shock resistant properties of molybdenum disilicide blades under centrifugal load
- An investigation to determine the heat-shock resistant properties of two molybdenum disilicide turbine blades under centrifugal loads imposed by turbine rotation is presented. Molybdenum disilicide turbine blades fabricated by hot-pressing techniques withstood heat-shock conditions under blade centrifugal stresses up to 5350 pounds per square inch. Additional development is required before the heat-shock resistant properties of molybdenum disilicide are satisfactory for turbine-blade application.
- Transonic-Wing Investigation in the Langley 8-Foot High-Speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2: Analysis of Pressure Distribution of Wing-Fuselage Configuration Having a Wing of 45 Degrees Sweptback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
- Report presenting a pressure-distribution investigation in the high-speed tunnel of a wing-fuselage configuration as part of an NACA research program to determine effects of wing geometry on aerodynamic characteristics and to explore the nature of flow over the configuration. Measurements were made on a fuselage and wing-fuselage combination for a range of Mach numbers. Results regarding accuracy, figures of pressure distributions, pressure distributions on the wing and fuselage, results at several angles of attack, section loading characteristics, normal-force characteristics, pitching-moment characteristics, pressure-drag characteristics, and fuselage skin-friction drag are provided.
- Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant
- Theoretical values of performance parameters for liquid hydrogen and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ration of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity. The maximum value of specific impulse was 364.6 pound-seconds per pound for a chamber pressure of 300 pounds per square inch absolute (20.41 atm) and an exit pressure of 1 atmosphere.
- Investigation of Effects of Grain Size Upon Engine Life of Cast AMS 5385 Gas Turbine Blades
- Report presenting an investigation to determine the effects of pouring temperature and grain size on the uniformity of lives and initial failure times of groups of AMS 5385 gas turbine blades and to relate the individual lives of the blades to grain size. This is due to the fact that the uniformity of lift of cast alloy gas-turbine blades is generally unsatisfactory. Results regarding the metallurgical examination are provided.
- Investigation of 16-inch impulse-type supersonic compressor rotor with turning past axial direction
- Report presenting an experimental investigation using a 16-inch impulse-type supersonic-compressor rotor as a separate component, which obtained a maximum total-pressure ratio of 5.42 and an adiabatic efficiency of 0.76 at 101-percent design speed. The rotor could operate over a wide range of back pressures, but it did not obtain the design impulse condition. Results regarding the rotor-component investigation and stage investigation are provided.
- Static Longitudinal Stability and Control Characteristics of a 1/16 -Scale Model of the Douglas D-558-II Research Airplane at Mach Numbers of 1.61 and 2.01
- Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the static longitudinal stability and control characteristics of a 1/16-scale model of the Douglas D-558-II research airplane. The results indicated a high degree of longitudinal stability that decreased slightly with increasing Mach number and lift coefficient.
- The effects of suction through porous leading-edge surfaces on the aerodynamic characteristics of a 47.5 degree sweptback wing-fuselage combination at a Reynolds number of 4.4 x 10(exp 6)
- A study investigated the effects of suction through porous leading-edge surfaces on the longitudinal aerodynamic characteristics of a 47.5 degree sweptback wing-fuselage configuration in the full-scale tunnel. The wing section normal to the quarter-chord line was NACA 64(sub 1)A112, the aspect ratio was 3.4, and the taper ratio was 0.51. Results regarding the basic wing characteristics and effect of area suction on the longitudinal characteristics are provided.
- Flight Investigation at Mach Numbers From 0.67 to 1.81 of the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing Missile Configuration Having an All-Movable Tail
- Report presenting a flight investigation of a small, all-movable tail to determine whether it is an effective longitudinal control for a cruciform, delta-wing missile at a range of Mach numbers from 0.67 to 1.81. The stability, control, hinge-moment, and drag characteristics are provided.
- Effect of fuel injectors and liner design on performance of an annular turbojet combustor with vapor fuel
- Report presenting a direct-connect duct investigation conducted with a one-quarter segment of a 25.5-inch-diameter annular combustor that had been developed for liquid fuel injection. The combustor was modified by changing the fuel injectors and liner design for vapor fuel injection. Results regarding accuracy and reproducibility, combustion efficiency, combustor-outlet temperature profiles, and pressure losses are provided.
- Review of High-Performance Axial-Flow-Compressor Blade-Element Theory
- This report presents a review of current compressor blade-element theory with particular emphasis on application to the transonic high-performance compressor. A discussion of the significant parameters of total-pressure loss and deviation angle is presented, and an indication of the extent of available knowledge and the problems involved in the determination of blade-element characteristics is given. Some recent results and considerations in this pursuit and suggestions for further avenues of investigation are indicated.
- Investigation of Pressure Recovery of a Single-Conical-Shock Nose Inlet at Mach Number 5.4
- An experimental investigation of the performance of a single-conical-shock diffuser was conducted at a Mach number of 5.4 and a Reynolds number based on model diameter of 375,000. Total-pressure recoveries of 13.7 and 13.1 percent were obtained at angles of attack of 0 degrees and 3 degrees, respectively. The corresponding kinetic energy efficiencies were 86.4 percent at an angle of attack of 0 degrees and 86.0 percent at an angle of attack of 3 degrees.
- Experimental and theoretical study of the interference at low speed between slender bodies and triangular wings
- Report presenting the aerodynamic characteristics of several wing-fuselage combinations measured at a Mach number of 0.25. Each combination consisted of a triangular wing with an aspect ratio of 2.0 and body of revolution with a fineness ratio of 12.5. Results regarding wings in the presence of bodies, wing-body combinations, and dorsal fins are provided.
- A Transonic Wind-Tunnel Investigation of an Unswept-Wing-Body Combination at Angles of Attack Up to 24 Degrees
- Report presenting testing of a wing with 0 degree sweepback of the 0.25-chord line in combination with a body of revolution at Mach numbers from 0.60 to 1.11 for angles of attack up to 24 degrees. Results regarding lift characteristics, pitching moment, drag characteristics, and lift-drag ratio are provided.
- Air-flow and thrust characteristics of several cylindrical cooling-air ejectors with a primary to secondary temperature ratio of 1.0
- Report presenting an investigation to determine the performance of 17 cooling-air ejectors at primary-jet pressure ratios from 1 to 10, secondary pressure ratios to 4.0, and a temperature ratio of unity. Results regarding pumping characteristics, effect of spacing ratio on pumping, effect of diameter ratio on pumping, thrust characteristics, effect of spacing ratio on thrust, effect of diameter ratio on thrust, comparison of cylindrical and conical ejectors, comparison of performance with small model ejectors, and a comparison of performance with full-scale installation are provided.
- The effect at high subsonic speeds of a flap-type aileron on the chordwise pressure distribution near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil section
- Report presenting an investigation in the high-speed tunnel to determine the effects on the chordwise pressure distributions of deflecting a flap-type aileron on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6.
- Performance Characteristics of a 24 Degree Straight-Outer-Wall Annular-Diffuser-Tailpipe Combination Utilizing Rectangular Vortex Generators for Flow Control
- An investigation of the performance characteristics of annular-diffuser designs applicable to turbojet afterburners. The best vortex-generator installations improved the diffuser static-pressure rise and downstream radial distributions without significantly altering the loss coefficients. Results regarding the axial inlet flow and whirling inlet flow are provided.
- Free-Spinning-Tunnel Investigation to Determine the Effect on Spins and Recoveries of Wing Leading-Edge Chord-Extensions and Drooped Leading-Edge Flaps on Scale Models of Two Sweptback-Wing Fighter Airplanes
- Report discussing an investigation to determine the effect of wing leading-edge chord-extensions and drooped leading-edge flaps on the spin and spin-recovery characteristics of models of two swept-wing fighter airplanes. The investigation included chord-extensions in the plane of the wing and chord-extensions deflected in combination with drooped leading-edge flaps. The chord extensions were not found to have an appreciable effect on spin or spin-recovery characteristics when installed in the plane of the wing.
- The Design of Brittle-Material Blade Roots Based on Theory and Rupture Tests of Plastic Models
- "Theoretical design charts based on Neuber's equations for symmetrically located notches are presented for estimating the approximate rupture strengths of blade roots made from brittle materials. The limit of applicability of the theoretical charts is shown as determined by rupture tests of plastic models. The optimum proportions among over-all root width, neck width, notch radius, and notch depth are determined from the design charts" (p. 1).
- Pressure and Force Characteristics at Transonic Speeds of a Submerged Divergent-Walled Air Inlet on a Body of Revolution
- Report presenting an investigation in the transonic tunnel on a submerged inlet with a divergent-walled approach ramp to determine flow phenomena, pressure recovery, and external forces to provide correlation with available data obtained on similar inlets. Results regarding the pressure characteristics, aerodynamic forces, and performance comparisons are provided.