From Introduction: "This paper presents the results of an investigation of force and moment characteristics for a wing with an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section parallel to the free stream."
From Introduction: "This paper presents the results of the investigation of the wing alone and of the wing-fuselage configurations employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A004 airfoil section parallel to the air stream. The experimental results of a wing of identical plan from having an NACA 65A006 airfoil section which was tested as part of the transonic program are presented in reference 1.
Report discussing an investigation of a parabolic body of revolution with and without the effects of an annular jet exhausting from the base. The aerodynamic characteristics, pressures, lift-curve slope, and other characteristics with the jet in operation and inoperative were compared.
Report presenting an investigation concerned with the measurement of the characteristics of longitudinal-control devices for a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. Most of the investigation was devoted to testing a 30-percent-chord, 50-percent-semispan elevon, but some used upper-surface spoilers. Results regarding the characteristics of the wing with the elevon undeflected and control-surface effectiveness are provided.
Report presenting an experimental investigation to determine the aerodynamic load distributions of a series of five bodies with conical or slightly blunted noses and cylindrical afterbodies in the 1- by 1-foot supersonic wind tunnel. Pressure distributions and viscous drags were measured at Mach number 3.12 for a range of Reynolds numbers and angles of attack.
Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.
Report presenting an analysis of the maximum power thrust-minus-drag performance of several turbojet-engine air-inlet combinations over a wide range of flight conditions. The primary objective of the analysis was to use the experimentally determined drag and total-pressure-recovery characteristics to show the range of satisfactory performance of each of several fixed-geometry inlet configurations. Results regarding the performance at 35,000 feet, inlet design considerations, speed range of efficient normal-shock inlet performance, effect of altitude on performance of the fixed-geometry system, and effect of nonstandard air on the performance of a fixed-geometry system are provided.
From Introduction: "The object of this report is to investigate the effects of after-burner lighting on the engine behavior and control-system requirements of a controlled turbojet engine. In this report, a simulation procedure for the afterburner is developed (based on ref. 3), this afterburner simulation is coordinated with previously developed nonafterburning-engine simulation procedures (ref. 4), and the compensated interacting control systems of references 1 and 2 are used. The results of an analog investigation of the the effects of an afterburner light on several controlled turbojet-engine configurations are reported and evaluated."
Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduction of adverse effects of propellers on longitudinal stability, and propulsive characteristics are provided.
Air was bled over the fifth-and tenth-stage rotor-blade rows through ports designed to pass 11 and 9 percent of the inlet flow, respectively, at 80 percent speed. Along the rated operating line the maximum speed at which rotating stall was encountered was lowered by either of these bleeds, and the stall patterns below these speeds were altered so that no dangerous resonant rotor-blade bending vibrations were excited. The combination of the two bleeds completely eliminated rotating stall to at least 50 percent speed. The compressor-discharge weight flow was decreased only at intermediate speeds, and the overall pressure ratio was affected only at intermediate speeds, and the overall pressure ratio was affected only by the combination bleed at intermediate speeds. Fifth-stage bleed increased compressor efficiency at low speeds, and tenth-stage bleed decreased efficiency at intermediate speeds.
From Introduction: "A survey of some of the advantages and problems associated with transpiration cooling of gas-turbine engines is given in reference 1, and its is shown therein that high pressure gradients around the periphery of gas-turbine blades require that the blade wall permeability be varied around the blade periphery in order for uniform cooling to be obtained over the entire blade surface. This fact is verified in experimental investigations of transpiration-cooled turbine blades mounted in a static cascade (references 2 and 3) where it is shown that although transpiration cooling results in extremely effective cooling in the midchord region of the blade, there are very large variations in the chordwise temperature distribution because of improper permeability variation."
From Introduction: "The rolling-pullout maneuver (any maneuver in which rolls occur during high g flight conditions) has been shown to be pertinent to design considerations from the standpoint of the loads produced on a vertical tail (refs. 1 to 3). In order to understand this problem better, the results of an analytical study of effects of large variations of some of the lateral-stability-derivative coefficients on the maximum angle of sideslip at first peak of its oscillation are presented in this paper. Also, expressions for estimating the effects of small variations of or errors in these coefficients on the maximum sideslip angle have been developed and are presented. "
"An investigation was conducted at Mach number 1.90 to determine pressure recovery and mass-flow characteristics of series of perforated convergent-divergent supersonic diffusers. Pressure recoveries as high as 96 percent were obtained, but at reduced mass flows through the diffuser. Theoretical considerations of effect of perforation distribution on shock stability in converging section of diffuser are presented and correlated with experimental data. A method of estimating relative importance of pressure recovery and mass flow on internal thrust coefficient basis is given and a comparison of various diffusers investigated is made" (p. 1).
Report presenting experiments in a 200-pound-thrust jet fuel-nitric acid rocket with an axial-flow igniter employing the hypergolic alkyl thiosphosphite-nitric acid system. No combustion instability was observed in the igniter, but many of the main-stage runs exhibited low-frequency oscillations.
From Summary: "A simple method is presented for estimating lift, pitching-moment, and hinge-moment characteristics of all-movable wings in the presence of a body as well as the characteristics of wing-body combinations employing such wings. In general, good agreement between the method and experiment was obtained for the lift and pitching moment of the entire wing-body combination and for the lift of the wing in the presence of the body. The method is valid for moderate angles of attack, wing deflection angles, and width of gap between wing and body."
Report presenting tests using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of four triangular-wing-fuselage models. Measurements of the normal force, chord force, and pitching moment for various angles of attack. Two models had wings of aspect ratio 2.31, one with an NACA 65-009 airfoil section and one with a 9-percent-thick biconvex section, and two with wings of aspect ratio 4, one with an NACA 65-006 airfoil and one with a 6-percent-thick double-wedge airfoil.
Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approach speed, comparison of flight and predicted approach speeds, and comparison of test pilots' and service pilots' approach speed are provided.
Report presenting lift and drag characteristics in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements using flight testing. Minimum comfortable approach speeds were evaluated by four test pilots. Suggestions for achieving optimal speeds for approach under various conditions are also provided.
Report presenting an investigation of the stress distribution in the roots of the first three stages of the J6S axial-flow compressor in order to explain root failures experienced in service. Root failures were producible in the lab when high vibratory stresses were combined with simulated centrifugal loads. Results regarding fatigue tests on the original J6S blade roots and on two redesigned blade roots as well as a comparison of the different root designs are provided.
Memorandum presenting the application of the concept of indicial functions to the analysis of the aerodynamic phenomena associated with the short-period pitching mode of wings in subsonic and supersonic flight. Simple physical relationships are pointed out and are used to study the effect on the rotary-damping-moment coefficient of changes in center-of-gravity position, Mach number, aspect ratio, plan form, frequency, and thickness.
"Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the one with a 7-percent-thick circular-arc airfoil section" (p. 1).
"The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint" (p. 1).
Report presenting an adhesive, FPL-710, which produces higher strength at temperatures up to 600 degrees Fahrenheit than previously obtained and possesses good resistance to aging at high temperatures. It also has acceptable resistance to creep and immersion in various organic solvents. Results regarding its strength properties, heating and aging resistances, and variables affecting bond strength are provided.
Report presenting a simplified limiting-blade-loading parameter for axial-flow-compressor blade elements derived from the application of a separation criterion used in two-dimensional boundary-layer theory to a typical suction-surface velocity distribution of a compressor blade element at design angle of attack. Results regarding two-dimensional cascade, compressor rotors, and compressor stators are provided.
Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the chordwise pressure distributions, wing-panel characteristics, wing-section characteristics, and maximum additional normal load on wing leading edge are provided.
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.
Memorandum presenting testing of a D-558-II airplane with the wing slats fully extended, with and without inboard wing fences, and with the wing slats half extended and wing fences removed. In order to improve the stick-force characteristics at moderate and large angles of attack, additional tests were conducted with two bungees of differing stiffness alternately attached to the control column.
Report presenting the effect of preinjection-fuel temperature on vaporization rates and combustion efficiency of a 16-inch ram-jet engine for two different fuels. Variation of the location of the fuel injectors and use of control sleeves were also explored.
From Summary: "A brief investigation was conducted in the altitude wind tunnel to determine the extent to which the afterburner shell cooling problem could be alleviated by internal configuration changes. Data were obtained with and without a cooling liner installed and for variations in the radial fuel distribution and in the radial distribution in flame-seat area. Consideration is given to the effects on both shell temperature and afterburner performance."
Report presenting an investigation in the 8- by 6-foot supersonic tunnel at a range of free-stream Mach numbers at zero angle of attack to determine the effects of internal corner fillets on the pressure recovery characteristics of twin-scoop conical-type inlets utilizing boundary layer removal and mounted on the RM-10 body. Without boundary layer removal, the use of fillets resulted in substantial improvements in pressure recoveries and near critical mass flows up to a certain Mach number.
Memorandum presenting an investigation in the supersonic blowdown tunnel to determine the effects of span and spanwise and chordwise location on the control characteristics of spoilers on a 6-percent-thick, 50 degrees sweptback wing of aspect ratio 2.5 and taper ratio of 0.625. The results of the investigation indicate that the inboard spoilers located at the rearward chordwise station produce the highest rolling-moment effectiveness.
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.
Theory and experiment were compared and found in good agreement for the elastic Buckling under combined stresses of long flat plates with integral waffle-like stiffening in a variety of configurations. For such flat plates, 45deg waffle stiffening was found to be the most effective of the configurations for the proportions considered over the widest range of combinations of compression and shear.
Memorandum presenting calculations made to determine the deceleration at any time after jettisoning of an airplane nose-section design typical of those which have been proposed as escape devices for high-speed airplanes. The decelerations were determined by two methods, one using successive approximations requiring graphical integration and the other giving reasonably close approximations by direct computation.
Report presenting an experimental two-dimensional investigation of the mechanism of the flow and losses involved in the operation of a low-solidity highly loaded turbine-blade profile suitable for use in an air-cooled turbine, which has been made in a cascade.
Memorandum presenting a five-stage axial-flow compressor with all rotor rows operating with transonic relative inlet Mach numbers designed as a research unit to study the potentialities and problems arising from the compounding of transonic stages. The report presents all design values and procedures, blade-row velocity diagrams, and the selection of blade shapes.
Memorandum presenting an evaluation of the overall performance of a 20-inch-diameter five-stage compressor as the initial step in an investigation of the potential performance and problems associated with a high-stage-pressure ratio compressor. The overall performance was evaluated over a range of flows at equivalent tip speeds from 40 to 100 percent of design. Results regarding the overall performance, compressor-inlet conditions, compressor-discharge conditions, stagewise variation of static pressure, and performance evaluation are provided.
Memorandum presenting an investigation of water spray cooling of turbine rotor blades with a representative centrifugal-flow turbojet engine. Water injection from several stationary configurations was investigated in order to determine the most favorable configuration on an overall basis. Results regarding blade temperature distributions, cooling efficiencies of various configurations, rotor blades failures, rotor blade spray patterns, and overall comparison of injection configurations are provided.
Report presenting information on landing gear applied drag loads and the nature of wheel spin-up in landing based on testing in the Langley impact basin. Particular attention is paid to the nature and variation of the coefficient of friction between the tire and runway during the wheel spin-up process. Results regarding the fundamentals of the process, comparison of maximum loads, variation of coefficient of friction, and effect of prerotation are provided.
Report presenting an investigation at a range of Mach numbers from 0.7 to 1.4 to determine the effect of scale on the zero-lift drag of a fin-stabilized body of revolution and a fighter-type airplane configuration. Results obtained at low values of Reynolds number were compared with larger scale data obtained on geometrically similar models in free flight. Results regarding fin-stabilized body and airplane model are provided.
Report presenting an exploratory investigation to determine the effects of wing slots on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage combination. Results regarding pitching-moment characteristics and lift and drag characteristics are provided.
"This report summarizes the effects of fuel volatility and engine design variables on the problem of starting gas-turbine engines at sea-level and altitude conditions. The starting operation for engines with tubular combustors is considered as three steps; namely, (1) ignition of a fuel-air mixture in the combustor, (2) propagation of flame through cross-fire tubes to all combustors, and (3) acceleration of the engine from windmilling or starting speed to the operating speed range. Pertinent data from laboratory researches, single-combustor studies, and full-scale engine investigations are presented on each phase of the starting problem" (p. 1).
Report presenting a supersonic flight investigation of a roll-stabilized acceleration control missile for a Mach number range from 1.4 to 1.7. The control system operation was found to be satisfactory and applicable to some present-day missiles using linear acceleration commands. Results regarding analysis, preflight simulator results, a comparison between simulator and analytical results, flight test results, and a comparison between the flight test and preflight simulator results are presented.
Report presenting an investigation of the flow properties of a constant-outer-wall annual diffuser in combination with a tailpipe in order to come up with a configuration suitable for turbojet afterburners. Information about axial inlet flow and whirling inlet flow is provided. During testing, a vena contrata region formed downstream from the center body terminal and rendered the first 1/2 diameter of the tailpipe ineffective.
Report presenting an investigation to measure the flying qualities of a high-performance personal-owner airplane to investigate the possible causes of instrument flying accidents with that type of aircraft. Testing indicated that the lack of aerodynamic stall warning and rapid roll-off at the stall could contribute to stall-spin accidents with high-performance personal-owner aircraft. Results regarding the handling qualities and the control under instrument flying conditions are provided.
Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles of attack from 0 degrees to 25 degrees are presented and compared with theory. Cones and ogives of fineness ratios 3 to 7 and two blunt-nosed body shapes with fineness ratios 3 and 5 were tested at Mach numbers from 2.75 to 5.00. Reynolds numbers were from 0.5 million to 6.4 million, depending on Mach number and body fineness ratio.
Report discussing a low-lift lateral stability investigation with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system at a range of Mach numbers. Results indicated that the system was nonlinear due to a large dead spot in the system. The primary effect of the system was to increase the damping of lateral oscillations.
Report presenting flight testing of two 7.5 degree boattail bodies of revolution with constant base annuli and varying jet static-pressure ratios and simulated turbojet exhaust rocket motors in order to determine the jet interference effects on total-drag and base-pressure coefficients over a range of Mach numbers. Results regarding the total drag and base-pressure and base-drag coefficients are provided.
Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.
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