From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."
Report discussing an investigation into the lateral-control characteristics and the pitching-moment characteristics of a scale model of the X-1 wing-fuselage configuration. Information about the estimated variation of rolling effectiveness and wing-fuselage pitching-moment coefficient is described in detail.
Report discussing testing to determine the aerodynamic characteristics of two semispan delta-wing configurations. Information about the lift characteristics, drag characteristics, pitching-moment characteristics, and comparison with other results is provided.
From Introduction: "The airfoil sections tested, which differ only in thickness ratio, were the NACA 64-006, 64-008, 64-010, and 641-012. Lift, drag, and pitching-moment data were obtained for Mach numbers of 0.3 to that for tunnel choke at angles of attack of -2^o to 31^o. The results of this investigation are reported herein."
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.
Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
"An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for small angles of attack. The measured mean skin-friction coefficients agreed well with theoretical values obtained for laminar flow over cones" (p. 1).
Report presenting an investigation at a Mach number of 1.61 to determine the control effectiveness characteristics of seven tip controls on a 60 degree delta wing. Pressure distribution measurements were made for a range of angles of attack and control deflections. Results regarding the effect of control deflection, effect of wing angle of attack, effect of hinge-line location, effect of fences, and effect of control size and location are provided.
Report discussing an investigation of a 45 degree swept-back-wing-body combination with flap spoiler ailerons, deflector ailerons, and a spoiler-slot-deflector aileron. The pressures were measured from Mach numbers 0.60 to 1.03 and at various angles of attack.
Memorandum presenting wind tunnel tests performed on a family of missiles. This paper summarizes some of the performance and stability and control characteristics of the missiles.
From Introduction: "Range in more or less steady level flight depends directly on aerodynamic lift-drag ratio at high supersonic speeds, just as it does at lower speeds. This result follows from the classical Breguet range equation in the case of powered flight, and it may be easily deduced from the equations of motion for unpowered or gliding flight (see refs. 1 and 2)."
From Introduction: "Results presented herein show the altitude performance of the turbine-propeller engine and its components and the applicability of the generalization method for predicting engine and component performance at altitudes other than the test altitude. Data from a brief investigation of windmilling and altitude starting characteristics of the engine also presented."
An investigation was made comparing the performance of JFC-2 fuel and unleaded, clear gasoline in a 3000-pound-thrust turbojet engine. The JFC-2 fuel was a blend of percent diesel fuel and 25 percent aviation gasoline. Engine combustion efficiency was equal to that obtained with gasoline at rated engine speed and altitudes up to 35,000 feet, but at lower engine speeds or at higher altitudes the JFC-2 fuel gave lower combustion efficiency. No discernible difference was obtained in starting or low-speed combustiion blow-out characteristics of the two fuels. Turbine-discharge radial temperature profiles were nearly the same at altitudes up to 35,000 feet.
Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach number of 0.19.
From Introduction: "The ram-jet missile studied in the present report is one type of shieldless which has the advantage of employing the simplest type of propulsion system."
"The over-all performance of a 16-stage axial-flow compressor was determined with various stator-blade resettings and a reduction in solidity of the rotor blades in the last three stages. It was shown that little control over the sudden change in slope of the surge-limit line at intermediate speeds was obtained with the blade modifications attempted, except that some change in speed at which the change in slope occurred could be effected by stator-blade resettings" (p. 1).
Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
From Summary: "Results of flight-path computations are presented for launchings from a straight deck and the curved ramp under conditions of insufficient lift at the instant of take-off."
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."
From Introduction: "This report presents data from measurements of the flow in a single-stage research compressor, which supports the model of reference 1. A calculated shock technique similar to that of reference 1 is incorporated with these experimental results. Another approach for estimating passage shock loss given a flow rate and blade geometry was reported in reference 2."
From Introduction: "The purpose of the present paper is to investigate the effect of two-speed gearing on the take-off efficiency under certain conditions. The present paper gives charts from which the efficiencies can be readily computed for optimum rotational speeds. Also included is a brief discussion of the static thrust of thin propellers, including the effect of camber on the static thrust."
From Introduction: "The engine evaluation of blends reported herein was conducted at the NACA Lewis laboratory. The data contained in references 2 to 14 are therefore summarized and the effect of the molecular structure of fuels on antiknock performance is shown in herein."
The time-average characteristics of boundary layers over a flat plate in nearly quasi-steady flow are determined. The plate may be either insulated or isothermal. The time averages are found without specifying the plate velocity explicitly except that it is positive and has an average value.
In a laboratory study of the factors involved in the influence of induction vacuum melting on 55ni-20cr-15co-4mo-3ti-3al heat resistant alloy, it was found that the major factor was the type of ceramic used as the crucible. The study concluded that trace amounts of boron or zirconium derived from reaction of the melt with the crucible refactories improved creep-rupture properties at 1,600 degrees F. Boron was most effective and, in addition, markedly improved hot-workability.
Report presenting calculations by the method of characteristics of 2960 boundaries of supersonic axisymmetric free jets exhausting from conically divergent nozzles into still air. The calculations covered a range of jet Mach numbers, a ratio of specific heats of the jet, divergence angles of the nozzle, and jet static-pressure ratios. Results regarding the effect of increasing the static pressure ratio, the simulation of one jet boundary by another, and interpolation and extrapolation of calculated boundaries are provided.
Spanwise lift distributions have been calculated for nineteen unswept wings with various aspect ratios and taper ratios and with a variety of angle-of-attack or twist distributions, including flap and aileron deflections, by means of the Weissinger method with eight control points on the semispan. Also calculated were aerodynamic influence coefficients which pertain to a certain definite set of stations along the span, and several methods are presented for calculating aerodynamic influence functions and coefficients for stations other than those stipulated. The information presented in this report can be used in the analysis of untwisted wings or wings with known twist distributions, as well as in aeroelastic calculations involving initially unknown twist distributions.
A method similar to that of NACA rep. 1000 is presented for calculating the effectiveness and the reversal speed of lateral-control devices on swept and unswept wings of arbitrary stiffness. Provision is made for using either stiffness curves and root-rotation constants or structural influence coefficients in the analysis. Computing forms and an illustrative example are included to facilitate calculations by means of the method. The effectiveness of conventional aileron configurations and the margin against aileron reversal are shown to be relatively low for swept wings at all speeds and for all wing plan forms at supersonic speeds.
Report presenting a cascade-general-momentum theory method for calculating the operating conditions of a supersonic propeller annulus throughout the flight Mach number range. General flow patterns about the cascade and adjustments to free-stream conditions are discussed.
The characteristics of a wedge static-pressure sensing element with various holder configurations were determined and compared with the characteristics of the conventional tube. The probes were tested over a range of Mach number from 0.3 to 0.95 and at various pitch and yaw angles. The investigation showed that the spike-mounted wedge sensing element has a pressure coefficient comparable with the conventional subsonic static-pressure probe and the pressure coefficient of the wedge varied less than that of the conventional probe for corresponding change of yaw angle.
From Summary: "Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly accurately predicted by the theory but that the actual center of pressure is more rearward than the theory indicates."
"As part of the Navy Project Zip to consider various boron-containing materials as possible high-energy fuels, the chemical and physical properties of Hi-Cal-2 prepared by the Callery Chemical Company were evaluated at the NACA Lewis laboratory. Elemental chemical analysis, heat of combustion, vapor pressure and decomposition, freezing point, density, self ignition temperature, flash point, and blow-out velocity were determined for the fuel. Although the precision of measurement of these properties was not equal to that obtained for hydrocarbons, this special release research memorandum was prepared to make the data available as soon as possible" (p. 1).
Report presenting a method for predicting the drag due to lift and lift-drag ratio of all-movable wing and body combinations and all-movable wings in the presence of bodies at supersonic speeds. The method is used to calculate the factors for configurations at which experimental data are available.
"A comparison is presented between the experimentally measured and theoretically calculated (by the method of NACA TN 3067) rates of roll of two rocket-propelled models with flexible rectangular wings. The comparisons show that although there are large aeroelastic losses in rolling rate, the theory predicts the actual rate of roll accurately" (p. 1).
"Free-flight drag measurements are presented which show the practicability of duplicating the zero-lift drag rise of many airplane configurations by simple bodies of revolution. The results confirm the transonic area rule for straight wings, and for delta and modified-delta wings with and without nacelles. The results showed that the area rule did not apply to one swept-wing configuration and an explanation is advanced to explain why it does not apply" (p. 1).
Report presenting an investigation to compare the characteristics of a full-span and a semispan highly swept wing in order to evaluate the general validity of the semispan wing testing technique. Results regarding the lift, drag, and pitching-moment characteristics are provided.
Report presenting a transonic investigation made by the free-fall technique of a plane wing and a cambered and twisted wing, each with an aspect ratio 6, taper ratio of 0.5, and a sweepback of 45 degrees. Measurements were made of the loads on the exposed wings, pressures on the fuselage in the vicinity of the wing, and acceleration and angle of attack of the complete model.
"An analysis is made of the effects of compressibility on the pressure coefficients about several bodies of revolution by comparing experimentally determined pressure coefficients with corresponding pressure coefficients calculated by the use of the linearized equations of compressible flow. The results show that the theoretical methods predict the subsonic pressure-coefficient changes over the central part of the body but do not predict the pressure-coefficient changes near the nose. Extrapolation of the linearized subsonic theory into the mixed subsonic-supersonic flow region fails to predict a rearward movement of the negative pressure-coefficient peak which occurs after the critical stream Mach number has been attained" (p. 1125).
Report presenting a comparison of the transonic aerodynamic characteristics of unswept and 45 degree sweptback wings in the high-speed tunnel and slotted tunnel. The purpose of the investigation was to explore the possibilities and limitations associated with transonic testing of relatively large wings in a rectangular slotted tunnel. Results regarding lift, pitching moments, drag, bending moments, and Schileren photographs are provided.
Memorandum compiling summaries from NACA reports on fuel that were published between July 1945 and 1952. The summaries are intended to be detailed enough to eliminate the need to obtain the complete report.
Report presenting the results from 20 hours of service operational flying of an instrumented North American F-100A fighter airplane. Results regarding the altitude and Mach number, normal-load factor, airplane attitude, use of controls, rolling motions, pitching motions, yawing motions, vertical-tail loads, horizontal-tail loads, and a comparison with other airplanes are provided.
Tests of a 1/5 scale model of a proposed 153-foot high-speed submarine have been conducted in the Langley full-scale tunnel at the request of the Bureau of Ships, Department of the Navy. The test program included: (1) force tests to determine the drag, control effectiveness, and static stability characteristics for a number of model configurations, both in pitch and in yaw, (2) pressure measurements to determine the boundary-layer conditions and flow characteristics in the region of the propeller, and (3) an investigation of the effects of propeller operation on the model aerodynamic characteristics. In response to oral requests from the Bureau of Ships representatives t hat the basic data obtained in these tests be made available to them as rapidly as possible, this data report has been prepared to present some of the more pertinent results. All test results given in the present paper are for the propeller-removed condition and were obtained at a Reynolds number of approximately 22,300,000 based on model length.
An analysis is made of the factors affecting the weight-flow rate per unit frontal area of centrifugal compressors with axial-flow vaned diffusers preceded by mixed-flow vaneless sections. It is shown that, for specified inlet conditions to the impeller and vaned diffuser, the weight-flow rate is increased at the expense of pressure ratio and vice versa. Charts are presented to help the designer make a satisfactory compromise between weight-flow rate and pressure ratio. Some conclusions of the investigation are : (1) Prewhirl is of negligible value in centrifugal compressors designed for high weight-flow rates.
"An experimental and analytical study has been made of some features of the turbulent heat diffusion behind a line heated wire stretched perpendicular to a flowing isotropic turbulence. The mean temperature distributions have been measured with systematic variations in wind speed, size of turbulence-producing grid, and downstream location of heat source. The nature of the temperature fluctuation field has been studied" (p. 1).
"Dynamic--response measurements for various conditions of displacement and rate signal input, sensitivity setting, and simulated hinge moment were made of the three control-surface servo systems of an NAES-equipped remote-controlled airplane while on the ground. The basic components of the servo systems are those of the General Electric Company type G-1 autopilot using electrical signal sources, solenoid-operated valves, and hydraulic pistons. The test procedures and difficulties are discussed" (p. 1).
Report presenting an experimental investigation in a one-sixth sector of an annular turbojet combustor to determine a method of controlling radial exhaust-gas-temperature distribution in a gas-turbine combustion chamber. The adjustment in controlling air was made by ducting the dilution air into the combustion zone in a predetermined manner through hollow radial struts or by modifying the basket-wall open-hole area. Results regarding the temperature distribution, temperature-rise efficiency, total-pressure loss, and altitude operating limits are provided.
"An investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-external compression inlet designed for a flight Mach number of 1.8, was conducted in the NACA Lewis 8-by 6-foot supersonic wind tunnel. Data were obtained at Mach numbers from 1.5 to 2.0 and angles of attack from 0 degrees to 10 degrees. Three exit nozzles were used; a cylindrical extension of the combustion chamber, a 4 degrees half-angle converging nozzle with a 0.71 contraction ratio, and a graphite converging-diverging nozzle having a 0.71 contraction ratio plus reexpansion to essentially major body diameter" (p. 1).
Report presenting an investigation to determine the effects of inlet-annulus blockage on compressor performance and its corresponding effect on the computed performance of a hypothetical engine. The hypothetical engine performance was calculated from the overall compressor performance and assumed component performance characteristics. Results regarding the compressor performance with no inlet blockage, effect of hub blockage on compressor performance and stall characteristics, effect of sector blockage on compressor performance, effect of hub blockage on computed engine performance, and design and control problems are provided.
Report presenting rotating-stall and blade-vibration data for the first three rotor blade rows of a 13-stage axial-flow compressor at several inlet temperatures. Stall patterns of 1 through 5 stall zones were detected at all inlet temperatures in the equivalent compressor speed ranges between 4600 and 6200 rpm.
"The effects of interaction between a landing gear and a flexible airplane structure on the behavior of the landing gear and the loads in the structure have been studied by treating the equations of motion of the airplane and the landing gear as a coupled system. The landing gear is considered to have nonlinear characteristics typical of conventional gears, namely, velocity-squared damping, polytropic air-compression springing, and exponential tire force-deflection characteristics. For the case where only two modes of the structure are considered, an equivalent three-mass system is derived for representing the airplane and landing-gear combination, which may be used to simulate the effects of structural flexibility in jig drop tests of landing gears" (p. 619).
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.
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