National Advisory Committee for Aeronautics (NACA) - 184 Matching Results
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- Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments
- Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain size, metallurgical studies of failed blades, stress-rupture tests, and hardness are provided.
- Preliminary Report on Experimental Investigation of Engine Dynamics and Controls for a 48-Inch Ram-Jet Engine
- Engine dynamics and controls data are presented for a ram-jet engine which was operated in a free-jet facility at a Mach number of 2.76 and altitudes from 68,000 to 82,000 feet. The predominant engine dynamic characteristics was dead time, with values ranging from 0.018 to 0.053 sec. The control systems were designed to hold a constant ratio of a diffuser static pressure to an inlet-cone reference static pressure.
- Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 2: stage performance with three different sets of stators
- Report presenting an impulse-type supersonic compressor designed for turning to the axial direction that was tested in air with three different sets of stator blades at eight angle settings.
- Experimental investigation of air-side performance of liquid-metal to air heat exhangers
- Report describing an experiment to obtain heat-transfer and pressure-drop data for the air side of a liquid-metal to air, shell-and-tube heat exchanger. Testing was conducted in a 500 kilowatt facility using sodium as the shell-side heating fluid. Results regarding the shell-and-tube heat exchanger and finned-tube heat exchanger friction factor are provided.
- Characteristics of a Hydraulic Control Determined from Transient Data Obtained with a Turbojet Engine at Altitude
- Memorandum presenting characteristics of a hydraulic control as determined by analyzing transient data obtained with a turbojet engine operating in the altitude wind tunnel. The excellent overall performance of the speed control is attributed to the elimination of large lags in the control system, thereby permitting the use of relatively high loop gains while still maintaining satisfactory damping in transients. Some information regarding the frequency-response analysis of speed control, simulation of speed control, and acceleration control are provided.
- Requirements for Auxiliary Stiffeners Attached to Panels Under Combined Compression and Shear
- "Panels of aluminum alloy sheets, framed by side and end stiffeners, were subjected to combined loading by means of offset knife edges applying loads to top and bottom end plates with reacting forces against the end plates supplied by laterally acting rollers. The test specimens were 17S-T aluminum alloy shoots 0.040 inch thick in panels of 10-inch width and three different lengths (approximately 10, 26, and 30 inch). Data were obtained for the bowing of transverse and longitudinal ribs of rectangular cross section and varying depths mounted on one side of the sheet only, for several ratios of compression to shear loads" (p. 1).
- Static longitudinal aerodynamic characteristics of a 52 degree sweptback wing of aspect ratio 2.88 at Reynolds numbers from 2,000,000 to 11,000,000
- Report presenting the effects of changes in Reynolds number on the longitudinal aerodynamic characteristics of a 52 degree sweptback wing with an aspect ratio of 2.88 and NACA 64(sub 1)-112 airfoil sections. The model was tested with the leading edge both smooth and rough. Results regarding force and pitching-moment results, flow observations, and discussion of force and moment characteristics are provided.
- Study of the canard configuration with particular reference to transonic flight characteristics and low-speed characteristics at high lift
- Report presenting a study of the flight characteristics of the canard configuration at transonic and supersonic speeds. Known problems concerning the low-speed characteristics of the canard are also investigated.
- Performance investigation of can-type combustor 1: instrumentation, altitude operational limits and combustion efficiency
- Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-pressure drop.
- Wind-Tunnel Investigation of Horizontal Tails 4: Unswept Plan Form of Aspect Ratio 2 and a Two-Dimensional Model
- Memorandum presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a horizontal-tail model of aspect ratio 2 with an unswept plan form and of a two-dimensional model. The two-dimensional model provides data which can be used as the basis for computing the three-dimensional lift and hinge-moment parameters by the lifting-surface-theory procedure. Results regarding the effectiveness and hinge-moment parameters, static longitudinal stability, scale effect, effect of standard roughness, and effect of removing the elevator nose seal are provided.
- The effects of Reynolds number at Mach numbers up to 0.94 on the loading on a 35 degree swept-back wing having NACA 65(1)A012 streamwise sections
- Report presenting an investigation of the effects of a variation of Reynolds number on the forces, moments, and surface pressures on a semispan model of a wing with 35 degrees of sweepback, an aspect ratio of 5, a taper ratio of 0.7, and the NACA 65(sub 1)A012 section in planes parallel to the plane of symmetry.
- The Effect of Surface Roughness on the Performance of a 23 Degree Conical Diffuser at Subsonic Mach Numbers
- Report of an investigation to determine the effect of surface roughness on the performance of a 23 degree conical diffusers with 2:1 ratio of exit to inlet area and a constant-area tail pipe. Information about the pressure survey results, including total-pressure-loss coefficient, diffuser effectiveness, and boundary-layer profiles is provided.
- Effects of Plan Form, Airfoil Section, and Angle of Attack on the Pressures Along the Base of Blunt-Trailing-Edge Wings at Mach Numbers of 1.41, 1.62, and 1.96
- Memorandum presenting an investigation at Mach numbers of 1.41, 1.62, and 1.96 to determine the effects of airfoil section and wing plan form on the pressures acting on the base of blunt-trailing-edge wings operating through an angle-of-attack range. The investigation included two groups of untapered wings of aspect ratio 2.7, with one group being unswept and the other with 45 degrees of sweepback. Results regarding the effects of wing location and body size, spanwise variations of base pressures, variations of average base pressure coefficients with angle of attack and wing section, and effects of plan form are provided.
- Dynamic corrosion of a stainless-steel specimen by water at 500 degrees F using a toroid circulating apparatus
- A slug of air-saturated distilled water was circulated for 317 hours at a velocity of 15 feet per second in an AISI 347 stainless-steel toroid with a wall temperature of 500 F and a 30 F difference in temperature between the hot and cold sections. The depth of corrosion layer was 0.001 inch (0.028 in./yr) in the hot sector and 0.0007 inch (0.019 in./yr) in the cold sector; no mass transfer was observed. The results of gas,water,and X-ray diffraction analyses are given together with photomicrographs of sections taken from the hot and cold sections of the specimen.
- Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 3: normal wedge inlet with semicircular cowl
- Report presenting an investigation of inlets utilizing two-dimensional compression wedges mounted normal to the fuselage surface with ram-type scoops for partial removal of the boundary layer. Two compression-wedge angles were included to simulate fixed positions of a variable-geometry configuration. Results regarding supersonic performance characteristics and subsonic and take-off performance characteristics are provided.
- Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3
- Report presenting the results of a free-flight investigation to determine the drag of circular, finite-length cylinders for a range of Mach numbers. For supersonic speeds, the drag of circular cylinders was found to be largely independent of fineness ratio and Reynolds number.
- Effect of Geometry on Secondary Flows in Blade Rows
- Memorandum presenting an investigation of the influence of blade-row geometry on secondary flows in a two-dimensional cascade by varying independently stagger angle, aspect ratio, solidity, and angle of attack and by providing blade fillets. Stagger angle and aspect ratio had no appreciable effect on this secondary flow, whereas solidity and angle of attack did affect the flow patterns indicating the turning as a major parameter.
- Effect of Engine and Control Limits on Steady-State and Transient Performance of Turbojet Engine With Variable-Area Exhaust Nozzle
- Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient performance, and some potential problems are provided.
- Low-Lift Buffet Characteristics Obtained From Flight Tests of Unswept Thin Intersecting Surfaces and of Thick 35 Degree Sweptback Surfaces
- Report presenting testing of two rocket-propelled research models to determine the effect of the intersection of thin aerodynamic surfaces and the effect of moderate sweepback of thick aerodynamic surfaces on low-lift buffeting. Results regarding trim changes and drag are also provided. It was discovered that low-lift buffeting may be induced at high subsonic speeds by interference due to the intersection of thin aerodynamic surfaces.
- Influence of a canard-type control surface on flow field in vicinity of symmetrical fuselage at Mach numbers 1.8 and 2.0
- Report presenting an experimental investigation of the flow field downstream of a canard-type control surface and in the vicinity of a symmetrical body in the 8- by 6-foot supersonic tunnel at Mach numbers of 1.8 and 2.0. The results indicated severe total pressure losses and large flow deflections in the control surface wake.
- An experimental investigation of the zero-lift pressure distribution over a wedge airfoil in closed, slotted, and open-throat tunnels at transonic Mach numbers
- Report presenting pressure distributions and Schileren photographs of the flow around a 10-percent-thick diamond airfoil at zero lift in two-dimensional closed, slotted, and open-throat tunnels. Results regarding the effect of slot area ratio and effect of slot spacing are provided.
- A Preliminary Investigation of the Static and Dynamic Longitudinal Stability of a Grunberg Hydrofoil System
- "A preliminary investigation has been made in order to determine the static and dynamic longitudinal stability characteristics and the force characteristics of a Grunberg hydrofoil system comprising a main lifting hydrofoil and planing-surface stabilizers. The tests showed that a rearward movement of the center of gravity decreased the static and dynamic stability but increased the lift-drag ratio. In smooth water, adequate static stability was observed for all conditions tested" (p. 1).
- Use of Fences to Increase Uniformity of Boundary Layer on Side Walls of Supersonic Wind Tunnels
- "An investigation of the use of solid fences installed on the side walls of a supersonic wind tunnel to retard the development of transverse flow and thus to increase the uniformity of the side-wall boundary layer is reported. Beneficial results were obtained with fences which had depths of the order of the boundary-layer displacement thickness and which followed potential-flow streamlines through the nozzle. Reduction of the number of fences on each side wall from four to two eliminated their effectiveness" (p. 1).
- Small-Scale Transonic Investigation of the Effects of Full-Span and Partial-Leading-Edge Flaps on the Aerodynamic Characteristics of a 50 Degree 38 Foot Sweptback Wing of Aspect Ratio 2.98
- Memorandum presenting a small-scale investigation of the effects of full-span and partial-span leading-edge flaps on the aerodynamic characteristics of a sweptback wing in the 7- by 10-foot tunnel over a Mach number range of 0.70 to 1.10. Lift, drag, pitching moment, and bending moment were obtained for the basic wing and for the wing with full-span and partial-span leading-edge-flap deflections of approximately 3, 6, and 9 degrees.
- Performance of air inlets at transonic and low supersonic speeds
- A general discussion of the air-inlet problem is presented. Recently obtained drag and pressure-recovery data for transonic-type nose, scoop, and wing-root inlets are summarized. Preliminary results concerning the performance of the sharp-edged supersonic-type inlets at transonic and subsonic speeds also are given.
- Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 1: two-dimensional compression-ramp inlets with semicircular cowls
- Report presenting an experimental investigation to determine the performance of twin-scoop side inlets located on the fuselage of a proposed aircraft in a region of large boundary-layer thickness. Inlet configurations with subsonic and supersonic cowlings which utilized two-dimensional compression ramps and ram-type scoops for boundary-layer-removal systems were investigated at several Mach number ranges. Results regarding supersonic Mach number range, angle of attack, subsonic Mach number, and static conditions are provided.
- Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 2: Preliminary Analysis of Overall Performance
- Report presenting an investigation of the overall performance of a 20-inch-tip-diameter 10-stage compressor as the initial step to examine the problems encountered in an axial-flow compressor with a high pressure ratio per stage. The investigation was carried out over a range of weight flows and percentages of the design speed. Results regarding the part-speed efficiency, surge characteristics, overspeed characteristics, compressor discharge Mach number, and stage characteristics are provided.
- Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics
- Report presenting an investigation to determine the low-speed longitudinal characteristics of an aspect ratio 4 triangular wing alone and in combination with a fuselage, vertical tail, and horizontal tail. The complete model consisted of a wing with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail, and two thin, unswept, all-movable horizontal tails of two different aspect ratios.
- Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance: transonic-bump method
- Report presenting an investigation to determine the control hinge moments and effectiveness at transonic speeds of a delta wing equipped with a constant-chord flap-type control with and without an unshielded triangular horn balance in the 7- by 10-foot tunnel using the transonic-bump method. The data indicated that the horn balance control was consistently more effective in changing lift at all Mach numbers than was the plain control but there was no appreciable difference in pitching-moment effectiveness.
- Altitude Investigation of Several Afterburner Configurations for the J40-WE-8 Turbojet Engine
- "An investigation was conducted in the Lewis altitude wind tunnel to evaluate the performance and operational characteristics of the J40-WE-8 afterburner. A brief program of minor modifications to the flame holder, diffuser, and fuel system was undertaken to improve at a burner-inlet pressure level of 620 pounds per square foot. At this pressure level, modifications to the fuel system resulted in an increase in maximum net thrust from 1500 to 1600 pounds and a reduction in specific fuel consumption in the stoichiometric region from 3.70 to 3.15 pounds of fuel per hour per pound of net thrust" (p. 1).
- Experimental Investigation of the Aerodynamic Characteristics of an Air-to-Air Missile Employing Cruciform Wings and Tail of Rectangular Plan Form at Mach Numbers of 1.4 and 1.9
- Memorandum presenting the aerodynamic characteristics of a model of an air-to-air missile employing variable-incidence cruciform wings of rectangular plan form and a fixed cruciform tail of rectangular plan form, an the characteristics of its body-wing and body-tail components, as determined from a wind-tunnel investigation for Mach numbers of 1.4 and 1.9. The results include normal-force, pitching-moment, and axial-force data for the body-wing-tail, body-wing, and body-tail combinations, and normal-force, hinge-moment, and axial-force data for the individual panels.
- Investigation of the Distribution of Lift, Drag, and Pitching Moment Between the Wing and Fuselage of a 1/30-Scale Semispan Model of the Bell X-5 Airplane at a Mach Number of 1.24 by the NACA Wing-Flow Method
- Report presenting an investigation at a Mach number of 1.24 to determine the distribution of lift, drag, and pitching moment between the wing and fuselage of a scale semispan model of the Bell X-5 airplane. Lift, drag, pitching moments, and wing bending moments were obtained for various angles of attack for 40 through 60 degrees sweptback duralumin wings in the presence of, but detached from, the fuselage.
- The Heat of Combustion of Tetraethyldiborane
- "The net heat of combustion of a sample of tetraethyldiborane was found to be 20,400 plus or minus 130 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water ,and solid boric oxide. The measurements were made in a Parr oxygen bomb calorimeter and the combustion is believed to have been 99 percent complete. A more reasonable value for the net heat of combustion would therefore be 20,600 plus or minus 130 Btu per pound" (p. 1).
- Free-Jet Investigation of a 20-Inch Ram-Jet Combustor Utilizing High-Heat-Release Pilot Burner
- Report presenting an investigation of the performance of a 20-inch-diameter ramjet engine with a high-heat-release pilot burner conducted at zero angle of attack in a free-jet test facility at a Mach number of 3.0. Two flame-holder configurations were used in conjunction with the high-heat-release pilot burner over a range of altitudes. Results regarding the performance of the high-heat-release pilot burner and performance of combustion-chamber configurations are provided.
- Investigation of a Chromium Plus Aluminum Oxide Metal-Ceramic Body for Possible Gas Turbine Blade Application
- "A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).
- Low-speed tests of a model simulating the phenomenon of control-surface buzz
- Report presenting low-speed tests of an airfoil model with a freely hinged flap attached to spoilers which passed through slots in the airfoil ahead of the hinge line. Testing indicated that buzz is not caused simply by buffeting of a flap by separated flow. Results regarding the oscillations experienced with the spoiler and flap in several positions are provided.
- Tests in the Ames 40- by 80-Foot Wind Tunnel of Two Airplane Models Having Aspect Ratio 2 Trapezoidal Wings of Taper Ratios 0.33 and 0.20
- Memorandum presenting tests of two airplane models with trapezoidal wings of aspect ratio 2 and taper ratios of 0.33 and 0.20. For each model, a fuselage with a fineness ratio of 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail was used. Tests of the wing-fuselage vertical-tail configuration and of the complete airplane model were made for both models.
- Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: comparison of three wings of aspect ratio 2 of rectangular, swept-back and triangular plan form, including effects of thickness distribution
- Report presenting the aerodynamic characteristics of three wing-body combinations with wings of aspect ratio 2 and rectangular, swept-back, and triangular plan form and a comparison at subsonic and supersonic speeds. All three wings had 3-percent-thick airfoil sections and were investigated with biconvex and rounded-nose airfoil sections. Results regarding the effects of wing plan form, effects of airfoil-section thickness distribution, and effects of Reynolds number are provided.
- Propeller Lift and Thrust Distribution From Wake Surveys of Stagnation Conditions
- Paper using the Bernoulli equation for nonsteady flow to derive formulas for propeller lift and thrust distribution in terms of wake-survey measurements of stagnation pressure rise through the propeller. Lift distributions and overall values of thrust from wake survey were compared with direct measurements of those values.
- Evaporation and Spreading of Isooctane Sprays in High Velocity Air Streams
- Memorandum presenting an investigation of the evaporation and spreading of isooctane sprays over a range of inlet-air conditions common in ram-jet engines. The total and liquid fuel distribution across the duct were determined. Over the specified ranges in the investigation, expressions were obtained which related the evaporation rate and degree of spreading of the sprays to the experimental variables.
- Preliminary drag and heat-transfer data obtained from air-launched cone-cylinder test vehicle over Mach number range from 1.5 to 5.18
- From Summary: "An air-launched cone-cylinder test vehicle designed to obtain data at Mach numbers above 4.0 was rocket boosted from a release Mach number of 5.18. The vehicle was launched at an altitude of 35,000 feet and reached peak velocity of 5150 feet per second at 28,500 feet. The total-drag coefficient (based on maximum cross-sectional area) decreased gradually from 0.31 at a Mach number of 1.75 to 0.145 at a Mach number of 5.18, while the Reynold's number (based on body length) increased from 31 x 10 to the 6th power to 107 x 10 to the 6th power."
- Design of apparatus for determining heat transfer and frictional pressure drop of nitric acid flowing through a heated tube
- "The object of the research project described herein is to present the design basis for test apparatus to determine the heat-transfer and pressure-drop characteristics of white fuming nitric acid flowing in a heated tube section. The heat flux to the tube will be of the order of magnitude occurring in a regeneratively cooled rocket engine" (p. 1).
- Jet effects on flow over afterbodies in supersonic stream
- From Summary: "Current NACA research on the subject of jet effects on the flow over afterbodies in a supersonic stream is briefly summarized. Several jet nozzle types installed in various afterbody configurations are considered for a wide range of operating conditions."
- Comparative Tensile Strengths at 1200 Degrees F of Various Root Designs for Cermet Turbine Blades
- Report presenting specimens of five different root designs, proportioned in accordance with the design surveys, and specimens of a conventional fir-tree turbine root were fabricated from a titanium carbide cement bonded with nickel. Comparative strengths were determined by short-term tensile tests at 1200 degree Fahrenheit. Results regarding blade root evaluation and rotor-segment evaluation are provided.
- Comparison of ignition delays of several propellant combinations obtained with modified open-cup and small-scale rocket engine apparatus
- From Summary: "Ignition delays of several propellant combinations obtained with a modified open-cup apparatus and with a small-scale rocket engine of approximately 50-pounds thrust were compared to study any correlations that might exist between the two methods of ignition-delay determination. The results were used in determining the relative utility of each apparatus."
- Lift, drag, and hinge moments at supersonic speeds of an all-movable triangular wing and body combination
- Report presenting hinge-moment data for a wing-body combination at Mach numbers of 1.46 and 1.99 and some lift and drag results for the lower Mach number. The model consisted of an aspect ratio 4, triangular, all-movable wing with an 8-percent-thick double-wedge section mounted on a pointed cylindrical body of fineness ratio 9-1/3. The results indicated that the wing has a relative effectiveness ranging from 63 to 98 percent.
- Burning rates of single fuel drops and their application to turbojet combustion process
- Report presenting burning rates for single isooctane drops suspended in various quiescent oxygen-nitrogen atmospheres at room temperature and pressure. The burning rates were compared with those predicted by a previously developed theory based on a heat- and mass-transfer mechanism and with values predicted by a modification to the theory.
- The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10-Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34 : TED No. NACA DE 31
- Memorandum presenting the results of a test on the transonic longitudinal characteristics of a scale rocket model of the McDonnell XF3H-1 airplane. The model, flown with a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane, was equipped with extensible rocket racks. Results regarding the Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.
- Thermal-Shock Resistance of a Ceramic Comprising 60 Percent Boron Carbide and 40 Percent Titanium Diboride
- Thermal-shock resistance of a ceramic comprising 60 percent boron carbide and 40 percent titanium diboride was investigated. The material has thermal shock resistance comparable to that of NBS body 4811C and that of zirconia, but is inferior to beryllia, alumina, and titanium-carbide ceramals. It is not considered suitable for turbine blades.
- Preliminary Results From a Limited Investigation of the Use of Controls During Service Operational Training With Fighter Airplanes
- Report presenting results from a limited investigation of the use of controls during service operational training with four fighter airplanes. The service pilots utilized the positive V-n envelope in performing their training missions but rarely approached the negative V-n envelope. Results regarding the operational V-n diagram for the F-86A, F-84G, F2H-2, and F-84G, design curves, maximum elevator rates, maximum aileron rates, rolling velocities, and control surface angles are provided.