National Advisory Committee for Aeronautics (NACA) - 13,806 Matching Results

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Investigation of ejection releases of an MB-1 rocket from a 0.04956-scaled model of the Convair F-106A airplane at Mach number 1.59
Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a model of the Convair F-106A airplane with its fin tips retracted at a simulated altitude of 18,670 feet. Successful ejections of the rocket were made at supersonic speeds by applying a combination of ejection velocity and nose-down pitching moment at release.
Investigation of flow coefficient of circular, square, and elliptical orifices at high pressure ratios
No Description Available.
Investigation of ejection release characteristics of four dynamically scaled internal-store shapes from a 1/17-scale simulated bomb bay of the Republic F-105 airplane at Mach numbers of 1.39 and 1.98
Report presenting an investigation of the release characteristics of dynamically scaled stores carried internally in a simulated bomb bay at Mach numbers of 1.39 and 1.98. A model of the Republic F-105 half-fuselage and bomb-bay configuration was tested with four store shapes: the MK-7 store, the bluff store, the TX-28 store, and turnabout TX-28 store. Results regarding ejection photographs and data plots are also provided.
Investigation of effects of various camouflage paints and painting procedures on the drag characteristics of an NACA 65 sub (421), sup -420, A = 1.0 airfoil section
No Description Available.
Exploratory Investigation of Performance of Experimental Fuelrich Hydrogen Combustion System
Exploratory investigation of performance characteristics of fuel-rich hydrogen combustor.
Experiments with fabrics for covering airplane wings
No Description Available.
Flight experiences and tests on two airplanes with suction slots
No Description Available.
Flight investigation at low angles of attack to determine the longitudinal stability and control characteristics of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose at Mach numbers from 1.2 to 2.1
Report presenting flight testing of a rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Results regarding the lift coefficient, dynamic stability, static stability, control effectiveness, and drag are provided.
A Flight Evaluation and Analysis of the Effect of Icing Conditions on the ZPG-2 Airship
A series of test flights was conducted by the U. S. Navy over a 3- year period to evaluate the effects of icing on the operation of the ZPG-2 airship. In supercooled. clouds, ice formed only on the forward edges of small protuberances and wires and presented no serious hazard to operation. Ice accretions of the glaze type which occurred in conditions described as freezing drizzle adversely affected various components to a somewhat greater extent. The results indicated, a need for protection of certain components such as antennas, propellers, and certain parts of the control system. The tests showed that icing of the large surface of the envelope occurred only in freezing rain or drizzle. Because of the infrequent occurrence of these conditions, the potential maximum severity could not be estimated from the test results. The increases in heaviness caused by icing in freezing rain and drizzle were substantial, but well within the operational capabilities of the airship. In order to estimate the potential operational significance of icing in freezing rain, theoretical calculations were used to estimate: (1) the rate of icing as a function of temperature and rainfall intensity, (2) the climatological probability of occurrence of various combinations of these variables, and (3) the significance of the warming influence of the ocean in alleviating freezing-rain conditions. The results of these calculations suggest that, although very heavy icing rates are possible in combinations of low temperature and high rainfall rate, the occurrence of such conditions is very infrequent in coastal areas and virtually impossible 200 or 300 miles offshore.
Flight characteristics
No Description Available.
Flight characteristics of a wingless rocket- powered model with four externally mounted air-to-air missiles at Mach numbers 0.7 to 1.6
Report presenting a flight investigation of four air-to-air missiles mounted by pylons on a rocket-powered basic wingless buffet-research vehicle to determine the trim, buffet, and drag characteristics of the combination.
Flexible petrol pipe
No Description Available.
Flight, analog-simulator, and analytical studies of an automatically controlled interceptor which uses a bank-angle-error computer for lateral commands
Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
A flight and analog study of the effect of elevating the radar-boresight axis upon stability and tracking performance of an automatically controlled interceptor
Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, and application of the principle of elevated radar-boresight axis are provided.
The Flettner rotor ship in the light of the Kutta-Joukowski theory and of experimental results
In this paper the fundamental principles of the Flettner rotor ship (Reference I) are discussed in the light of the Kutta-Joukowski theory and available experimental information on the subject. A brief exposition of the Kutta-Joukowski theory is given and the speed of the rotor ship Buckau computed, first by using effective propulsive force obtained by the above theory, and then by direct application of wind tunnel data.
Experiments with fabrics for covering airplane wings, to determine effect of method of installation
No Description Available.
Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint
No Description Available.
Flight Instrument for Measurement of Liquid-Water Content in Clouds at Temperatures Above and Below Freezing
A principle formerly used in an instrument for cloud detection was further investigated to provide a simple and rapid means for measuring the liquid-water content of clouds at temperatures above and below freezing. The instrument consists of a small cylindrical element so operated at high surface temperatures that the impingement of cloud droplets creates a significant drop in the surface temperature. ? The instrument is sensitive to a wide range of liquid-water content and was calibrated at one set of fixed conditions against rotating multicylinder measurements. The limited conditions of the calibration Included an air temperature of 20 F, an air velocity of 175 miles per hour, and a surface temperature in clear air of 475 F. The results obtained from experiments conducted with the instrument indicate that the principle can be used for measurements in clouds at temperatures above and below freezing. Calibrations for ranges of airspeed, air temperature, and air density will be necessary to adapt the Instrument for general flight use.
Flight test of a solid-fuel ramjet with the internal surface of the combustor air cooled
Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. The internally cooled combustor averted combustor burn-out during the flight test. Results regarding the net thrust coefficient, gross thrust coefficient, time history of the air specific impulse, and total fuel load are provided.
A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance
Effects of manual attack-display noise filtering on pilot tracking performance.
Flight test of an end-burning solid-fuel ramjet
Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse 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.
A Photographic Study of Freezing of Water Droplets Falling Freely in Air
From Summary: "A photographic technique for investigating water droplets of diameter less than 200 microns falling freely in air at temperatures between 0 C and -50 C has been devised and used to determine: (1) The shape of frozen droplets, (2) The occurrence of collisions of partly frozen or of frozen and liquid droplets, and (3) The statistics on the freezing temperatures of individual free-falling droplets."
Full-scale wind-tunnel tests of a 35 deg swept-wing fighter airplane with a spoiler- slot-deflector lateral control system
Wind tunnel tests of swept-wing fighter aircraft with spoiler-slot-deflector lateral control system.
Full-Scale Wind-Tunnel Tests of a North American FJ-3 Airplane with a Spoiler-Slot-Deflector Lateral Control System
Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.
High altitude performance investigation of J65-B-3 turbojet engine with both JP-4 and gaseous hydrogen fuels
No Description Available.
High efficiency of seaplanes
A table is presented which includes data for calculating the index of efficiency. The author uses this data to conclude that seaplanes cannot be considered inferior to terrestrial airplanes.
High-altitude cooling. 3 : Radiators
Report details the methods of determining the heat-transfer rate, pressure drop, and drag power of high-altitude radiators. Performance charts are provided for a wide range of design variables.
High altitude flying
This note investigates the effect of high altitude or low atmospheric pressure upon the operation of an engine and the effect of the low pressure and lack of oxygen and of the very low temperatures upon the pilot and upon the performance of the airplane itself.
High-altitude performance of J71-A-11 turbojet engine and its components using JP-4 and gaseous-hydrogen fuels
Report presenting data to determine the component and overall engine performance up to an altitude limit for the J71-A-11 (600-B36) turbojet engine. Engine operation using JP-4 fuel at Mach number 0.8 was satisfactory up to an altitude of about 60,000 to 65,000 feet, and engine operation with marginal combustion stability was maintained to an altitude of about 80,000 feet. Results regarding the altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall engine performance losses, exhaust-nozzle-area requirements, and altitude performance at rated engine conditions 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
Flutter characteristics of three low-aspect-ratio all-movable half-span control surfaces at Mach numbers from 1.49 to 2.87.
Investigation of lithium hydride and magnesium as high-temperature internal coolants with several skin materials
Lithium hydride and magnesium as high temperature internal coolants with skin materials.
Investigation of Icing Characteristics of Typical Light Airplane Engine Induction Systems
The icing characteristics of two typical light-airplane engine induction systems were investigated using the carburetors and manifolds of engines in the horsepower ranges from 65 to 85 and 165 to 185. The smaller system consisted of a float-type carburetor with an unheated manifold and the larger system consisted of a single-barrel pressure-type carburetor with an oil-jacketed manifold. Carburetor-air temperature and humidity limits of visible and serious Icing were determined for various engine power conditions. Several.methods of achieving ice-free induction systems are discussed along with estimates of surface heating requirements of the various induct ion-system components. A study was also made of the icing characteristics of a typical light-airplane air scoop with an exposed filter and a modified system that provided a normal ram inlet with the filter located in a position to Induce inertia separation of the free water from the charge air. The principle of operation of float-type carburetors is proved to make them inherently more susceptible to icing at the throttle plate than pressure-type carburetors.. The results indicated that proper jacketing and heating of all parts exposed to the fuel spray can satisfactorily reduce or eliminate icing in the float-type carburetor and the manifold. Pressure-type carburetors can be protected from serious Icing by proper location of the fuel-discharge nozzle combined with suitable application of heat to critical parts.
An investigation of jet effects on adjacent surfaces
From Summary: "The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit."
Investigation of Aerodynamic and Icing Characteristics of Water-Inertia-Separation Inlets for Turbojet Engines
The results of an investigation of several internal water-inertia-separation inlets consisting of a main duct and an alternate duct designed to prevent automatically the entrance of large quantities of water into a turbojet engine in icing conditions are presented. Total-pressure losses and icing characteristics for a direct-ram inlet and the inertia-separation inlets are compared at similar aerodynamic and simulated icing conditions. Complete ice protection for inlet guide vanes could not be achieved with the inertia-separation inlets investigated. Approximately 8 percent of the volume of water entering the nacelles remained. In the air passing into the compressor inlet. Heavy alternate-duct-elbow ice formations caused by secondary inertia separation resulted in rapid total-pressure losses and decreases in mass flow. The duration in an icing condition for an inertia-separation- inlet, without local surface heating, was increased approximately four times above that for a direct-ram inlet with a compressor-inlet screen. For normal nonicing operation, the inertia-separation- inlet total-pressure losses were comparable to a direct-ram installation. The pressure losses and the circumferential uniformity of the mass flow in all the inlets were relatively independent of angle of attack. Use of an inertia-separation inlet would in most cases require a larger diameter nacelle than a direct-ram inlet in order to obtain an alternate duct sufficiently large to pass the required engine air flow at duct Mach numbers below 1.0 at the minimum area.
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
Aerodynamic characteristics of aircraft configuration having tail surfaces outboard of wing tips at supersonic speeds - wind tunnel stability test.
Interference effects of fuselage-stored missiles on inlet duct model of an interceptor-type aircraft at Mach numbers 1.5 to 1.9
No Description Available.
Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing
Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Investigation of Adjustable Supersonic Inlet in Combination With J34 Engine Up to Mach 2.0
Pressure recovery in adjustable supersonic inlet combined with J34 turbojet engine up to Mach 2.0.
Investigation of Aerodynamic and Icing Characteristics of a Flush Alternate Inlet Induction System Air Scoop
An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet. The investigation was made over a range of mass-air- flow ratios of 0 to 0.8, angles of attack of 0 and 4 deg airspeeds of 150 to 270 miles per hour, air temperatures of 0 and 25 F various liquid-water contents, and droplet sizes. The ram inlet gave good pressure recovery in both clear air and icing but rapid blockage of the top-deck screen occurred during icing. The flush alternate inlet had poor pressure recovery in both clear air and icing. The greatest decreases in the alternate-inlet pressure recovery were obtained at icing conditions of low air temperature and high liquid-water content. No serious screen icing was observed with the alternate inlet. Pressure and temperature distributions on the carburetor top deck were determined using the preheat-air supply with the preheat- and alternate-inlet doors in various positions. No screen icing occurred when the preheat-air system was operated in combination with alternate-inlet air flow.
Investigation of afterburner combustion screech and methods of its control at high combustor pressure levels
Control of high pressure combustion screech in afterburner.
Interference of multiplane wings having elliptical lift distribution
In calculating the self-induction of a wing surface, elliptical lift distribution is assumed, while in calculating the mutual induction or interference of two wing surfaces, a uniform distribution of the lift along the wing has hitherto been assumed. Whether the results of these calculations are substantially altered by assuming an elliptical lift distribution (which is just as probable as uniform distribution) is examined here.
An Instrument Employing a Coronal Discharge for the Determination of Droplet-Size Distribution in Clouds
A flight instrument that uses electric means for measuring the droplet-size distribution in above-freezing clouds has been devised and given preliminary evaluation in flight. An electric charge is placed on the droplets and they are separated aerodynamically according to their mass. Because the charge placed on the droplets is a. function of the droplet size, the size spectrum can 'be determined by measurement of the charge deposited on cylinders of several different sizes placed to intercept the charged droplets. An expression for the rate of charge acquisition by a water droplet in a field of coronal discharge is derived. The results obtained in flight with an instrument based on the method described indicate that continuous records of droplet-size spectrum variations in clouds can be obtained. The experimental instrument was used to evaluate the method and was not refined to the extent necessary for obtaining conclusive meteorological data. The desirable features of an instrument based on the method described are (i) The instrument can be used in clouds with temperatures above freezing; (2) the size and the shape of the cylinders do not change during the exposure time; (3) the readings are instantaneous and continuous; (4) the available sensitivity permits the study of variations in cloud structures of less than 200 feet in extent.
An instrument for recording the position of airplane control surfaces
N.A.C.A. has developed an instrument which makes a continuous record of the angular position of the control surfaces of an airplane, not only in steady flight but during acrobatics as well. It has proven useful in researches into stability and controllability, and from records obtained from it many otherwise obscure details of piloting technique have been available for the instruction of pilots, from novices to seasoned experts.
Investigation of a 1/22-scale model of the Republic F-105 airplane in the Langley 8-Foot transonic tunnel: lateral, directional, and additional longitudinal static stability and control
Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 at Mach numbers from 0.60 to 1.13. The primary focus of this report are the static lateral and directional stability and control characteristics of the model. Results regarding force and moment results, longitudinal characteristics, lateral and directional characteristics.
Investigation of a 1/22-scale of the Republic F-105 airplane in the Langley 8-foot transonic tunnel: Static longitudinal stability and control and performance characteristics at transonic speeds
Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.
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
Internal flow performance of fixed 14 deg ramp inlet from zero to 20 deg angle of attack at supersonic free stream.
Investigation of ejection releases of an MB-1 Rocket from a 0.04956-scaled model of the Convair F-106A airplane at Mach number 1.59
Report presenting an investigation of the ejection release characteristics of the MB-1 rocket from the missile bay of a Convair F-106A airplane. Results regarding pitching moment, ejections, release conditions, and missile trajectory are provided.
Investigation of Ejection Releases of an MB-1 Rocket from a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Altitudes
As a continuation of an investigation of the ejection release characteristics of an internally carried MB-1 rocket in the Convair F-106A airplane, fin modifications at additional Mach numbers and simulated altitudes have been studied in the 27- by 27-inch preflight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The MB-1 rocket was ejected with fins open, fins closed, fins closed with a shroud around the fins, and fins folded with a "boattail" placed in between the fins. Dynamically scaled models (0.0^956 scale) were tested at simulated altitudes of 12,000, 18,850, and 27,500 feet at subsonic Mach numbers and at 18,850, 27,500, and 40,000 feet for Mach numbers of 1-39, 1-59, and 1.98. Successful ejections can be obtained for over 10 store diameters from release point by the use of a shroud around the folded fins with the proper ejection velocity and nose-down pitching moment at release. In one case investigated it was found desirable to close off the front one-third of the bomb bay. It appeared that the fins should be opened after release and within 5 "to 6 rocket diameters if no modifications are made on the rocket. An increase in fuselage angle of attack caused higher nose-up pitch rates after release.
An investigation of ejection releases of submerged and semisubmerged dynamically scaled stores from a simulated bomb bay of a fighter-bomber airplane at supersonic speeds
Report presenting an investigation of the release characteristics of several dynamically scaled store shapes from a simulated bomb bay at Mach numbers of 1.39, 1.60, and 1.98. A streamline store, a blunt-nose store with wedge-type fins of low aspect ratio, and a bluff store with a skirt were tested. Results regarding pitching motions, ejection velocity, effect of increase in altitude, and addition of plate or spike to the nose of the store are provided.