National Advisory Committee for Aeronautics (NACA) - 74 Matching Results
Search Results
- The aerodynamic characteristics at transonic speeds of a model with a 45 degree sweptback wing, including the effect of leading edge slats and a low horizontal tail
- Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge slats on the aerodynamic and longitudinal stability characteristics of a model of a swept-wing fighter-type airplane. Two different spanwise extents of leading-edge slats were tested, from 35 to 95 percent semispan and from 46 to 95 percent semispan. Results regarding the lift characteristics, drag characteristics and lift-drag ratios, stability characteristics, and flow-study pictures are provided.
- Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41
- Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = 1.41 in the 4- by 4-foot supersonic pressure tunnel. Modifications to the configuration included variation of the body length and canard area and the substitution of a series of very small span wings for the cruciform delta wings and canard controls.
- Aerodynamic characteristics of two flat-bottomed bodies at Mach number of 3.12
- From Introduction: "This report presents the results of an investigation in the NACA Lewis 1- by 1-foot supersonic wind tunnel of two flat-bottomed bodies to determine their aerodynamic characteristics at a Mach number of 3.12."
- An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds
- The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.
- Analysis of the turbojet for propulsion of supersonic bombers
- From Introduction: "The investigation is discussed in the present report is an analysis of the turbojet engine as the power plant for bombers capable of supersonic flight speeds. A similar analysis, in which the turbojet engine is considered for the propulsion of supersonic fighter aircraft, is presented in reference 1. Two plans are considered in this report."
- Application of Radial-Equilibrium Condition to Axial-Flow Turbomachine Design Including Consideration of Change of Entropy With Radius Downstream of Blade Row
- Report presenting an investigation of the validity of application of the simplified-radial-equilibrium equation to axial-flow turbomachines. Two different types of equations were used. Results regarding the interpretation of the data, single stages, middle and end stages of the multistage compressor, application of the radial-equilibrium equation, and the solution for the velocity distributions are provided.
- Blow-out velocities of various petroleum, slurry, and hydride fuels in a 1 7/8-inch diameter combustor
- Report presenting testing using a 1 7/8-inch inside-diameter combustor that can measure and compare the blow-out velocities of single-component fuels, slurries, and fuel mixtures with a wide range of reactivity and physical properties. The blow-out velocities of isooctane, n-heptane, isopentane, allyl chloride, and propylene oxide varied int he same way as flame speeds of the fuels. Results regarding the effects of different additives are also provided.
- A calculation study of wing-aileron flutter in two degrees of freedom for two-dimensional supersonic flow
- Report presenting the results of some sample calculations for the bending-aileron and torsion-aileron flutter of an idealized wing-aileron system for several values of Mach number in supersonic flow and some subsonic Mach numbers. The results are preliminary but may provide some knowledge of the influence of variations in certain parameters and to indicate some of the differences in the trends at high and low speeds.
- Coefficient of friction and damage to contact area during the early stages of fretting 2: steel, iron, iron oxide, and glass combinations
- Report presenting experiments to study the start of fretting and cause of damage during the early stages of fretting of steel-steel combinations at a frequency 5 cycles per minute, an amplitude of 0.006 inch, a load of 150 grams, in air with relative humidity of less than 10 percent. Pure iron, glass, and iron oxide powder compacts were used in supplementary experiments.
- Combined Natural- and Forced-Convection Laminar Flow and Heat Transfer of Fluids With and Without Heat Sources in Channels With Linearly Varying Wall Temperatures
- Note presenting an analysis of the flow of fluids with and without heat sources and subject to body forces between two plane parallel surfaces which are oriented in the direction of the generating body force under the condition that the temperature vary linearly along these surfaces. Results regarding the velocity and temperature distributions, heat transfer, and fluid flow are provided.
- Comparison between theory and experiment for interference pressure field between wing and body at supersonic speeds
- Report presenting pressure-distribution data for a wing-body combination at several Mach and Reynolds numbers to investigate the effects of wing-body interference. The model was a single-wedge, rectangular wing mounted on a cylindrical body with an ogival nose. Results regarding the general physical principles, effects of angle of attack, effect of wing-incidence angle, effect of Reynolds number, and comparison with theory from other sources are provided.
- Comparison of experimental with calculated results for the lifting effectiveness of a flexible 45 degree sweptback wing of aspect ratio 6.0 at Mach numbers from 0.8 to 1.3
- Report presenting tests conducted on models with 45 degree sweptback wings with varying degrees of flexibility to determine the effective lift-curve slopes in order to evaluate the usefulness of a general method for predicting effective lift ratio by a comparison of predicted values with test results.
- Dynamic Stability and Control Characteristics of a Ducted-Fan Model in Hovering Flight
- Report presenting the results of an experimental investigation of the dynamic stability and control of a simple ducted-fan model in hovering flight in order to provide basic information on the stability and control of jet vertically rising airplanes in hovering flight. The investigation primarily consisted of flight tests with the model hovering at altitude and near the ground.
- The Effect of a Change in Body Shape on the Loading of a 45 Degree Sweptback Wing-Body Combination at Transonic Speeds
- Memorandum presenting an investigation made in the 8-foot transonic tunnel of the pressure distribution on a wing-body combination with a 45 degree sweptback wing with aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The chordwise pressure distributions, which were determined at various spanwise stations, indicate that the flow about the two configurations is the same. Results regarding basic pressure measurements and loading and aerodynamic characteristics are provided.
- Effect of ignitor design and ignitor spark-gap environment on ignition in a turbojet combustor
- Report presenting an investigation to determine the effect of ignitor design and ignitor spark-gap environment on the ignition-energy requirements of a single tubular turbojet engine combustor. Data were obtained for a range of altitude inlet-air pressures, two-air flow rates, a range of combustor-inlet air and fuel temperatures, and two fuels. The effects on ignition energy requirements of shielding the ignitor spark gap, fuel heating elements and auxiliary fuel fields, and gap width and ignitor spark-gap immersion depth were investigated.
- Effect of Jet-Nozzle-Expansion Ratio on Drag of Parabolic Afterbodies
- The interaction of the flow from one convergent and two convergent-divergent nozzles on parabolic afterbodies was studied at free-stream Mach numbers of 2.0, 1.6, and 0.6 over a range of jet pressure ratio. The influence of the jet on boattail and base drag was very pronounced. Study of the total external afterbody drag values at supersonic speeds indicated that, over most of the high-pressure-ratio range, increasing the nozzle design expansion ratio increased the drag even though the boattail area was reduced. Increasing the pressure ratio tended to increase slightly the total-drag increment caused by angle-of-attack operation.
- The Effect of Magnesium Particles of Various Equivalent Diameters on Some Physical Properties of Petrolatum-Stabilized Magnesium-Hydrocarbon Slurries
- Memorandum presenting the effect of magnesium particles of various equivalent diameters on the apparent viscosity, sedimentation ratio, and redispresibility of petroleum-stabilized magnesium-JP-4 slurries. Powders of the following equivalent diameters were investigated: 2.8, 3.8, 7.2, 9.3, 12.0, and 14.8 microns. An analysis of the experimental error and reproducibility of values of apparent viscosity, sedimentation ratio, and redispersibility of the slurries was also made.
- Effect of Nozzle Secondary Flows on Turbine Performance as Indicated by Exit Surveys of a Rotor
- Report presenting detailed circumferential and radial surveys of total pressure and total temperature made downstream of the turbine rotor of a high-speed, high-specific-mass-flow turbine at design operating conditions. The purpose of this testing was to determine the sources and magnitudes of losses in turbines. Results regarding total pressure ratio, total-temperature-drop ratio, contours of efficiency, and location of the losses are provided.
- Effect on the low-speed aerodynamic characteristics of a 49 degree sweptback wing having an aspect ratio of 3.78 of blowing air over the trailing-edge flap and aileron
- Report presenting an investigation in the full-scale tunnel to determine the effects on the aerodynamic characteristics of a 49.1 degree sweptback wing of blowing a high-energy stream of air over a trailing-edge flap and an aileron. The results indicated that significant increases in lift coefficient and an improvement in aileron effectiveness may be obtained by the blowing method of boundary-layer control.
- Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections
- Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.
- Effects of Operating Propellers on the Wing-Surface Pressures of a Four-Engine Tractor Airplane Configuration Having a Wing with 40 Degrees of Sweepback
- Memorandum presenting an investigation to evaluate the effects of operating propellers and of nacelles on the wing-surface pressures on a semispan model of a four-engine tractor airplane configuration with a 40 degree sweptback wing and aspect ratio of 10. Results regarding the effects of the nacelles with the propellers off, effects of flaps, and effects of operating propellers are provided.
- Effects of sweep and thickness on the static longitudinal aerodynamic characteristics of a series of thin, low-aspect-ratio, highly tapered wings at transonic speeds: transonic-bump method
- An investigation by the transonic-bump technique of the static longitudinal aerodynamic characteristics of a series of thin, low-aspect-ratio, highly tapered wings has been made in the Langley high-speed 7- by 10-foot tunnel. The Mach number range extended from about 0.60 to 1.18, with corresponding Reynolds numbers ranging from about 0.75 x 10(6) to 0.95 x 10(6). The angle of attack range was from -10 degrees to approximately 32 degrees.
- The effects of wing-mounted external stores on the trim, buffet, and drag characteristics of a rocket-propelled model having a 45 degree sweptback wing
- Memorandum presenting a rocket-propelled model flown to determine the effects of four wing-mounted bomb-type external stores on the trim, buffet, and drag characteristics of a wing-fuselage configuration with a 45 degree sweptback wing. The model is compared with data from a similar model without stores. Results regarding trim, buffet, lift and stability, and drag are provided.
- Experimental Effects of Propulsive Jets and Afterbody Configurations on the Zero-Lift Drag of Bodies of Revolution at a Mach Number of 1.59
- The present investigation was made at a free-stream Mach number of 1.59 to compare the afterbody drags to a series of conical boattailed models at zero angle of attack. Afterbody drags were obtained for both the power-off and the power-on conditions. Power-on drags were obtained as a function of afterbody fineness ratio, jet pressure ratio and divergence, and jet Mach number.
- Experimental influence coefficients for the deflection of the wing of a full-scale, swept-wing bomber
- Report presenting the results of deflection tests on the wing of a full-scale, swept-wing jet bomber in the form of structural influence coefficients relating the deflection of a system of points on the wing and concentrated loads applied on the wing spars. The procedures for determining the coefficients are included.
- An Experimental Investigation at Low Speeds of the Effects of Lip Shape on the Drag and Pressure Recovery of a Nose Inlet in a Body of Revolution
- Report presenting wind-tunnel tests of a body of revolution with a circular nose inlet conducted at low speeds to ascertain some of the effects of inlet lip bluntness and profile on diffuser performance and body drag. Testing occurred at free-stream Mach numbers up to 0.330 with inlet flows from zero to choking and a steady 0 degree angle of attack and angle of yaw. Results regarding the internal-flow studies with the strut-mounted model and drag and surface-pressure studies with the sting-supported model are provided.
- Experimental Investigation of Rotating Stall and Blade Vibration in the Axial-Flow Compressor of a Turbojet Engine
- Report presenting a compressor-blade-vibration survey on a production turbojet engine incorporating an axial-flow compressor with a pressure ratio of approximately 7. The investigation was conducted with three different guide-vane assemblies and four jet-nozzle sizes. The correlation of rotating stall and blade vibration were determined using calculations.
- Experimental Investigation of the Aerodynamic Characteristics of a Ballistic-Type Missile
- Memorandum presenting lift, drag, and pitching-moment coefficients of a ballistic-type missile configuration as determined from tests in the 10- by 14-inch supersonic wind tunnel at a range of Mach numbers and angles of attack. Pressure distributions and drag coefficients were also determined at 0 degrees angle of attack.
- Experimental Investigation of the Damping in Roll of Cruciform Triangular Wing-Body Combinations at Mach Numbers From 1.5 to 6.0
- Report presenting measurements of the damping in roll of cruciform triangular wings of aspect ratios 0.64, 1.28, and 2.31 at supersonic Mach numbers from 1.5 to 6.0. The models were launched from rifled guns and the time history of the model roll position in free flight was explored. Results regarding the comparison with theory, transonic effects, and comparison with results at other facilities are provided.
- An Experimental Investigation of the Flutter of Several Wings of Varying Aspect Ratio, Density, and Thickness Ratio at Mach Numbers From 0.60 to 1.10
- Memorandum presenting an experimental investigation to determine the flutter characteristics of several rectangular wings of variable aspect ratio at a range of Mach numbers. The wings were solid aluminum or steel and were 2, 4, and 6 percent thick. Results regarding the flutter at low and high angles of attack are provided.
- Experimental Permeability Measurements on a Strut-Supported Transpiration-Cooled Turbine Blade with Stainless-Steel Shell made by the Federal-Mogul Corporation under Bureau of Aeronautics Contract N0as 51613-C
- A turbine blade with a porous stainless-steel shell sintered to a supporting steel strut has been fabricated for tests at the NACA by Federal-Mogul Corporation under contract from the Bureau of Aeronautics, Department of the Navy. The apparent permeability of this blade, on the average, more nearly approaches the values specified by the NAGA than did two strut-supported bronze blades in a previous investigation. Random variations of permeability in the present blade are substantialy greater than those of the bronze blades, but projected improvements in certain phases of the fabrication process are expected to reduce these variations.
- An experimental study of porosity characteristics of perforated materials in normal and parallel flow
- Report presenting an experimental investigation to determine the porosity characteristics of perforated materials in normal and parallel flow. The results indicted that the porosity of material is governed principally by its open ratio, but that density has a slight effect.
- An extension of the investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61
- Report presenting an investigation of the effects of heat transfer on boundary-layer transition at higher Reynolds numbers, greater amounts of heating, and a more extensive study of the effects of surface irregularities than what was published in a previous report. Report presenting tests with a smooth model and tests with surface roughness and tunnel flow disturbance are provided.
- Flight investigation of the effects of a partial-span leading-edge chord extension on the aerodynamic characteristics of a 35 degree swept-wing fighter airplane
- Report presenting a flight investigation to evaluate the effects of a partial-span, 15-percent-chord, leading-edge extension on the aerodynamic characteristics of the F-86A airplane. Results regarding the longitudinal stability, low-speed stalls, drag, and pilot reports are provided.
- Flight Investigation to Evaluate the Roll-Rate Stabilization System of the Naval Ordnance Test Station SIDEWINDER Missile at Mach Numbers From 0.9 to 2.3
- Report presenting a flight investigation using a rocket-powered model to evaluate the roll-rate stabilization of the Naval Ordnance Test Station SIDEWINDER missile, which uses aerodynamic damping by gyro-actuated rollerons. Dynamic roll instability was found to occur in flight.
- Free-Flight Zero-Lift Drag Results from a 1/5-Scale Model and Several Small-Scale Equivalent Bodies of Revolution of the Convair F-102 Configuration at Mach Numbers up to 1.34
- From Summary: "A 1/5-scale, rocket-propelled model of the Convair F-102 configuration was tested in free flight to determine zero-lift drag at Mach numbers up to 1.34 and at Reynolds numbers comparable to those of the full-scale airplane. This large-scale model corresponded to the prototype airplane and had air flow through the duct. Additional zero-lift drag tests involved a series of small equivalent bodies of revolution which were launched by means of a helium gun."
- Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads
- Report presenting an investigation to determine the effects of location of bodies (finned and unfinned) on the aerodynamic characteristics of unswept- and swept-wing--fuselage models and to determine the aerodynamic loads on the bodies in the presence of the wings. Results for the complete model characteristics and for the body are provided.
- Lateral control characteristics of two structural similar flexible wings with 45 degrees sweep: a sweptback wing and a wing with M plan form
- Report presenting a low-speed wind-tunnel investigation to determine the static longitudinal control characteristics of flap-type and retractable spoiler-type ailerons on a rigid sweptback wing, a flexible sweptback wing, and a flexible M-wing. Results regarding the rigid-wing and flexible-wing characteristics for each plan form are also provided.
- Lift and moment coefficients expanded to the seventh power of frequency for oscillating rectangular wings in supersonic flow and applied to a specific flutter problem
- From Summary: "Linearized theory for compressible unsteady flow is used to derive the velocity potential and lift and moment coefficients in the form of oscillating rectangular wing moving at a constant supersonic speed. Closed expressions for the velocity potential and lift and moment coefficients associated with pitching and translation are given to seventh power of the frequency. These expressions extend the range of usefulness of NACA report 1028 in which similar expressions were derived to the third power of the frequency of oscillation. For example, at a Mach number of 10/9 the expansion of the potential to the third power is an accurate representation of the potential for values of the reduced frequency only up to about 0.08; whereas the expansion of the potential to the seventh power is an accurate representation for values of the reduced frequency up to about 0.2. The section and total lift and moment coefficients are discussed with the aid of several figures. In addition, flutter speeds obtained in the Mach number range from 10/9 to 10/6 for a rectangular wing of aspect ratio 4.53 by using section coefficients derived on the basis of three-dimensional flow are compared with flutter speeds for this wing obtained by using coefficients derived on the basis of two-dimensional flow."
- Maneuver accelerations experienced by five types of commercial transport airplanes during routine operations
- "The magnitude and frequency of occurrence of maneuver accelerations experienced by five types of commercial transport airplanes during routine operations have been obtained from time-history (VGH) records and are presented herein. The results are compared with available gust-acceleration data for the operations considered. It is indicated that maneuver accelerations may contribute substantially to the total load histories of transport airplanes, particularly in the case of medium-altitude operations" (p. 1).
- Measurements of Normal-Force-Coefficient Fluctuation on Four 9-Percent-Thick Airfoils Having Different Locations of Maximum Thickness
- Memorandum presenting a two-dimensional wind-tunnel investigation of the effects of maximum-thickness location on fluctuating pressures and normal-force coefficients on 9-percent-thick airfoils, which indicated that for normal-force coefficients up to 0.6, the section variables had little effect on the pressure pulsations and root-mean-square normal-force-coefficient fluctuations. Results regarding pressure fluctuations and normal-force-coefficient fluctuations are provided.
- A method for measuring the product of inertia and the inclination of the principal longitudinal axis of inertia of an airplane
- Report presenting a simple method of experimentally determining the product of inertia and the inclination of the principal longitudinal axis of inertia of an airplane. The results of the method are provided and a description of the equipment and techniques are given for a simple model and a conventional airplane. Results regarding moments of inertia about the body reference area, the product of inertia and inclination of the principal axis, and the principal moments of inertia are provided.
- Note on the Aerodynamic Heating of an Oscillating Surface
- Note presenting an analysis of the temperature distributions in a fluid over an oscillating surface with heat transfer and associated heat-transfer parameters are compared with those for the case of conduction at a stationary surface with the same initial temperature potential. It was found that the heat transfer for the oscillating surface can be considerably different from that for conduction alone.
- Note on the Effects of First-Order Aerodynamic Loads on Propeller Shaft Loads with Emphasis on Counterrotating Propellers
- An investigation of the 1XP excitation of inclined single-rotation propellers has indicated a new concept for determining propeller shaft forces and moments of an inclined propeller. This report presents preliminary results, in particular to the counterrotating propeller.
- On the Sound Field of a Point-Shaped Sound Source in Uniform Translatory Motion
- A rigorous analysis presented of the excitation of sound by point sources moving in uniform translatory motion at subsonic or supersonic velocities through a two- or three-dimensional medium at rest. The construction of surfaces of constant phase is based upon Huyghens' principle in such a manner that the propagation in the medium at rest of the elementary waves emanating from the sound source is independent of the momentary state of motion of the sound source. Hence, characteristic traits of the sound propagation may be understood even on the basis of simple geometric constructions.
- Organophosphorus Compounds in Rocket-Engine Applications
- Report discussing the ignition-delay determinations of three organophosphorous fuels with nitric acid oxidants at simulated altitude conditions with a small-scale rocket engine.
- Organophosphorus compounds in rocket-engine applications
- Report presenting experimental ignition-delay determinations of mixed alkyl thiophosphites, triethyl trithiophsphite, and propylene N,N-dimethylamidophosphite with red and white fuming nitric acid conducted at a range of temperatures and pressure altitudes. The literature pertaining to the use of organo-phosphorous compounds in rocket-propellant combinations was surveyed and summarized with emphasis on ignition-delay investigations.
- Preliminary Altitude Operational Characteristics of a J57-P1 Turbojet Engine
- "The operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes between 15,000 and 66,000 feet in the Lewis altitude wind tunnel. Included in this study is a discussion of fuel nozzle coking, the altitude operating limits with and without the standard engine control, the compressor surge characteristics, and the engine starting and windmilling characteristics. Severe circumferential turbine outlet temperature gradients which occurred at high altitude as a result of fuel nozzle coking were alleviated by the manufacturer's change in the fuel flow divider schedule and in a nozzle gasket material" (p. 1).
- Preliminary Altitude Performance Characteristics of the J57-P-1 Turbojet Engine with Fixed-Area Exhaust Nozzle
- An investigation to determine the altitude performance of the J57-P-1 turbojet engine and components was conducted at the NACA Lewis altitude wind tunnel. Data were obtained over a corrected inboard rotor speed range from 56 to 106 percent of rated speed, with intercompressor bleeds both open and closed, at altitudes from 15,000 to 50,000 feet and at a flight Mach number of 0.81. The corresponding range of Reynolds number indices was from 0.858 to 0.213. All data presented were obtained with a fixed-area exhaust nozzle sized according to the manufacturer's specification. Over-all engine performance parameters are presented as functions of inboard rotor speed corrected on the basis of engine inlet temperature. Component parameters are presented as functions of their respective corrected rotor speeds. A tabulation of all performance data is included in addition to the graphical presentation. Corrected net thrust is unusually sensitive to changes in corrected inboard rotor speed in the high speed region. A change of 1 percent in speed, at sated speed, produced a change of 6 percent in corrected net thrust . At rated engine speed, increasing the altitude from 15,000 to 50,000 feet at a constant flight Mach number of 0.81 increased the specific fuel consumption 13 percent but did not affect corrected net thrust.
- Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine
- Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled, dynamic submarine model. Two types of control systems were evaluated. Results regarding the qualitative analysis of the control system, dive paths, equations of motion, and comparison with experimental paths are provided.