National Advisory Committee for Aeronautics (NACA) - 5,157 Matching Results
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- Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine
- Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.
- Method for Estimating Lift Interference of Wing-Body Combinations at Supersonic Speeds
- Memorandum presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations adapted to combinations with other than triangular wings. The methods are applied to the prediction of the lit-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.
- Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75
- Report presenting a free-jet investigation of the performance, burner-shell cooling, and ignition characteristics of a flight-weight 48-inch-diameter XRJ47-W-5 ramjet engine at an inlet Mach number of 2.75 and an angle of attack of 3 degrees. Data were obtained over a range of altitudes, inlet temperatures, and fuel-air ratios.
- Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
- Memorandum presenting a transonic flutter investigation of models of the wing of a current fighter airplane. The models were dynamically and elastically scaled in accordance with criteria which include a flutter safety margin. Results regarding the presentation of data, interpretation of results, wings without leading-edge chord-extensions, and wings with leading-edge chord-extensions are provided.
- Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1
- Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.
- Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor
- Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.
- Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane
- Memorandum presenting an investigation of the steady-state wing loads conducted on a Boeing B-52 airplane over a range of Mach numbers and altitudes. Results regarding flight tests and air-load calculations are provided.
- Altitude Performance of a Turbojet Engine Using Pentaborane Fuel
- Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments are provided.
- Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
- Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
- Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds
- Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
- Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
- Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0.
- 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
- Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.
- Analyses for Turbojet Thrust Augmentation With Fuel-Rich Afterburning of Hydrogen, Diborane, and Hydrazine
- Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine was computed. Results regarding takeoff thrust augmentation and flight thrust augmentation are provided.
- Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds
- Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.
- Determination of Rate, Area, and Distribution of Impingement of Waterdrops on Various Airfoils From Trajectories Obtained on the Differential Analyzer
- "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil - angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders" (p. 1).
- Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01
- Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.
- Stability and Control Characteristics at Low Speed of a 1/10-Scale Model of MX-1554A Design
- Report discussing an investigation of the low-speed stability and control characteristics of a model of the proposed MX-1554A design with a triangular wing and triangular stabilizing surfaces. It also includes the effect of wing incidence, slotted flaps, wing and tail height, external tanks and speed brakes, ground board, spoilers, tip ailerons, flaps, differential tail deflection, and an unswept wing on stability, control, aerodynamic, longitudinal, and lateral characteristics.
- Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01
- Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.
- Some Effects of Aeroelasticity on the Rolling Effectiveness of a 10-Percent-Scale Model of the Mcdonnell F-101A Airplane Wing at Mach Numbers From 0.5 to 1.2
- Report discussing testing of the effects of aeroelasticity on the rolling effectiveness on a model of a McDonnell F-101A airplane wing. The aeroelastic losses varied based on the Mach number and altitude.
- Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design
- Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stability derivatives, and a single support strut on the stability, control, and aerodynamic characteristics.
- Stability and Control Characteristics at High Subsonic Speeds of a 1/30-Scale Model of the MX-1554A Design
- Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.
- Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle
- Report discussing an investigation of the effect of curved speed brakes on the drag characteristics and longitudinal stability and control characteristics of a model of the MX-1554A with a circular jet nozzle. The speed brakes were tested at several deflections, gaps, and locations in the landing configuration and clean configuration. Results of a lateral- and directional-stability study due to reduction in the vertical tail area are also provided.
- Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53
- Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coefficients, neutral points, directional stability, and positive effective dihedral is provided.
- Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane
- Report presenting an investigation of the low-speed stability and control characteristics of a 1/15-scale free-flying model of the Convair XB-58 airplane. Results regarding the longitudinal stability and control and a pod-drop investigation are provided.
- Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane
- Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.
- Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01
- "A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger" (p. 1).
- Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds
- Report discussing available wind-tunnel data on low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations with unswept and sweptback wings. The effects of variations of tail position, wing plan form, airfoil section, trailing-edge flaps, stall-control devices, and ground interference on air-flow characteristics an tail contribution are also described.
- Transonic Aerodynamic and Trim Characteristics of 1/15-Scale Models of the Convair MX-1964 Airplane With Indented Fuselage
- Report presenting an investigation of two scale models of the MX-1964 airplane with indented fuselage conducted in the transonic tunnel. One model had a plane delta wing with full-span elevons and the other had a cambered delta wing with partial-span elevons. Results regarding the aerodynamic characteristics and effect of elevon deflection are provided.
- Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane
- Report discussing the results of an investigation to determine the low-speed power-off stability and control characteristics of a model of the Bell D-188A VTOL airplane. The static stability and control characteristics were generally satisfactory except above certain angles of attack and aileron effectiveness dropped off as the angle of attack was increased. Modifications for increasing the directional stability by altering the vertical tails are also described.
- A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds
- Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
- Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats
- Memorandum presenting a wind-tunnel investigation of a high-wing airplane with an aspect ratio 6.75 wing with approximately 36 degrees of sweepback in order to determine the lift effectiveness obtainable with trailing-edge blowing flaps in combination with leading-edge slats. Close to theoretical flap effectiveness was obtained with blowing flaps deflected 45, 55, and 65 degrees at low angles of attack. Results regarding the wind tunnel, take-off performance, landing performance, and comparisons with flight data are provided.
- Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25
- Aerodynamic characteristics of rectangular platform, all-movable controls combined with slender body of revolution at Mach 3 to 6.25. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.
- An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion
- Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.
- Nonuniform Burnup and Poisoning Effects in a Reactor and Validity of Uniform Approximation
- Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.
- The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61
- Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The store was separately sting-mounted on its own six-component internal balance and was traversed through a wide systematic range of spanwise, chordwise, and vertical positions.
- Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
- Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.
- Summary of Subsonic-Diffuser Data
- Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.
- Combustion Performance of Two Experimental Turbojet Annular Combustors at Conditions Simulating High-Altitude Supersonic Flight
- Performance of experimental annular turbojet combustors at simulated high altitude supersonic flight conditions.
- Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-Aspect-Ratio Swept-Back Wing-Stability and Control
- Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.
- Performance of Isentropic Nose Inlets at Mach Number of 5.6
- Memorandum presenting an investigation of the performance of inlet configurations with a forebody designed for isentropic external compression at a nominal Mach number of 5.6. At zero angle of attack, all the configurations yielded larger total-pressure recoveries than had previously been obtained with a single-conical-shock inlet. Results regarding the flow about the forebody, inlet performance, and performance comparisons are provided.
- Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From
- "An investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane has been conducted at Mach numbers from 0.6 to 1.5 by the Langley Pilotless Aircraft Research Division by utilizing rocket-propelled test vehicles. No effects of mutual interference between the midspan spoiler and the outboard aileron were detectable. Above the speed of sound, the ailerons were relatively ineffective as compared with the spoiler because of wing twisting" (p. 1).
- Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds
- Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.
- The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations 2 - Swept-wing Heavy-bomber Configuration With Large Store Nacelle. Lateral Forces and Pitching Moments, Mach Number, 1.61
- Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6. Separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The configuration investigated simulated a heavy bomber airplane with a large store or nacelle with frontal area equivalent to a twin-engine nacelle.
- The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 6. - Swept-Wing Heavy-Bomber Configuration With Stores of Different Sizes and Shapes
- Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with stores of several shapes and sizes.
- Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds
- Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
- Dynamic Stability Investigation of Two Right Circular Cylinders in Axial Free Flight at Mach Numbers From 0.4 to 1.7 Fineness-Ratio- 2.56 Cylinder and Fineness-Ratio-4.0 Cylinder With Flared Afterbody
- Memorandum presenting two right circular cylinders tested in axial free flight over a Mach number range of 0.4 to 1.7 by using the rocket-boosted-model technique. Results regarding time history, basic data cross plots, center of pressure, and drag are provided.
- Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds
- "The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).
- 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
- Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
- Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
- Memorandum presenting an investigation of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. Results regarding titanium models, stainless-steel models (uncoated), stainless-steel models coated with aluminum oxide, solution effects on the decomposition temperature of lithium hydride, effect of lithium hydride and magnesium on temperature measurements, and efficiency of models cooled with lithium hydride are provided.
- Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0
- Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.