National Advisory Committee for Aeronautics (NACA) - 151 Matching Results
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- Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds
- Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coefficient are described at Mach 1.0 and the greatest Mach number of 1.37.
- Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation
- Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps induced when full open at low airspeeds. The propulsive thrust of the exhaust-ejector installation was calculated to be slightly less than the thrust of the collector-ring-installation.
- High-Speed Wind-Tunnel Tests of a Model of the Lockheed YP-80A Airplane Including Correlation with Flight Tests and Tests of Dive-Recovery Flaps
- "This report contains the results of tests of a 1/3-scale model of the Lockheed YP-90A "Shooting Star" airplane and a comparison of drag, maximum lift coefficient, and elevator angle required for level flight as measured in the wind tunnel and in flight. Included in the report are the general aerodynamic characteristics of the model and of two types of dive-recovery flaps, one at several positions along the chord on the lower surface of the wing and the other on the lower surface of the fuselage. The results show good agreement between the flight and wind-tunnel measurements at all Mach numbers" (p. 1).
- An Investigation of the Effects of Sweep on the Characteristics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel
- "An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper ration of 2.5:1.0, has been tested with no sweep, and 30 deg and 45 deg of sweepback and sweepforward in conjunction with a typical fuselage at Mach numbers from 0.60 to 0.96 at angles of attack generally between -2 deg and 10 deg in the Langley 8-foot high-speed tunnel. Sweep was obtained by rotating the wing semispans about a point in the plane of symmetry. The normal-force, pitching-moment, profile-drag, and loading characteristics for the wings have been obtained from pressure measurements and wake surveys" (p. 1).
- Ditching Tests with a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail
- "Tests were made with a 1/16 size dynamically similar model of the Navy XP2V-1 airplane to study its performance when ditched. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated" (p. 1).
- Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes Within Thunderstorms September 17, 1946 to September 18, 1946 at Orlando, Florida
- The results obtained from measurements of gust velocities, draft velocities, and ambient-air temperature within thunderstorms for the period September 17, 1946 to September 18, 1946 at Orlando, Fla. are presented herein. These data are summarized in tables I, II, and III, respectively, and are of the type presented in reference 1 for previous flights.
- Canopy loads investigation for the F6F-3 airplane
- Report presenting an investigation of surface static pressures over the outer and inner surfaces of the cockpit canopies on the Grumman F6F-3, Curtiss SB2C-4E, and Grumman F8F-1 airplanes in the full-scale tunnel. Results regarding the external pressure distribution and internal static pressure are provided.
- A Low-Speed Investigation of an Annular Transonic Air Inlet
- Report presenting an investigation of three transonic fuselage-inlet installations designed to maintain substream velocities on the body ahead of air inlets. Surface pressures and inlet total pressures were measured at the tops of the test configurations for wide ranges of inlet-velocity ratio and angles of attack. Results indicated that substream velocities were maintained on all three noses over the angle of attack ranges and inlet-velocity ratio useful for high-speed flight.
- Estimate of Hull-Weight Change with Varying Length-Beam Ratio for Flying Boats
- "A study has been made of the variation of seaplane hull weight with length-beam ratio in a systematic series of hulls designed for constant gross weight and similar spray characteristics. It is found that increases in the length-beam ratio bring about small reductions in the hull weight if it is assumed that seaplanes having the same weight and bottom shape will be designed for the same load factor. A short discussion is also given to show the reduction in load factor that may occur with high length-beam ratios" (p. 1).
- Force Tests of the Boeing XB-47 Full-Scale Empennage in the Ames 40- by 80-Foot Wind Tunnel
- A wind-tunnel investigation of the Boeing XB-47 full-scale empennage was conducted to provide, prior to flight tests, data required on the effectiveness of the elevator and rudder. The XB-47 airplane is a jet-propelled medium bomber having wing and tail surfaces swept back 35 degrees. The investigation included tests of the effectiveness of the elevator with normal straight sides, with a buldged trailing edge, and with a modified hinge-line gap and tests of the effectiveness of the rudder with a normal straight-sided tab and with a bulged tab.
- Investigation of High-Lift and Stall-Control Devices on a NACA 64-Series 42 Degree Sweptback Wing With and Without Fuselage
- Report presenting an investigation of a 42 degree sweptback wing of aspect ratio 4, taper ratio 0.625, and NACA 64-series airfoil sections to study several proposed devices for increasing the maximum lift coefficient and improving the longitudinal stability characteristics of sweptback wings at the stall. Some of the devices tested included leading-edge flaps and slats, trailing-edge split and extended split flaps, upper-surface split flaps, and upper-surface fences. The results regarding the characteristics of the devices and the wing-fuselage combinations are described.
- Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections
- Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
- Wing-flow tests of a triangular wing of aspect ratio two 1: effectiveness of several types of trailing-edge flaps on flat-plate models
- Report presenting an investigation of the problem of applying controls to low-aspect-ratio wings of triangular plan form by using the NACA wing-flow method with parallel-sided models with sharp leading and trailing edges. Results regarding the data analysis, Reynolds number and separation effects, flap effectiveness, plan-form characteristics, angle of zero lift, and triangular plan-form flying-wing characteristics are provided.
- Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet
- Memorandum presenting a flight investigation conducted on a 20-inch-diameter steady-flow ramjet at a range of altitudes and free-stream Mach numbers. Results regarding the variation of combustion efficiency with fuel-air ratio and pressure altitude, effects of combustion-chamber-inlet velocity, and altitude on the operating range of fuel-air ratio are provided. The ramjet unit operated smoothly over the entire range of velocities and altitudes with the exception of occasional rough operation at excessively rich mixtures.
- Indirect Methods for Obtaining Ram-Jet Exhaust-Gas Temperature Applied to Fuel-Metering Control
- Memorandum presenting an analytical method developed that gives two independent means of obtaining the total-temperature ratio across a ram jet or across a turbojet tail-pipe burner without direct measurement of the final gas temperature. Experimental verification of the analysis has been obtained with a 20-inch ram jet over a wide range of operating conditions.
- Wind-Tunnel Investigation of the Stability of Jettisoned Nose Sections of the D-558 Airplane: Phases 1 and 2
- Report presenting an investigation of the stability of models of the jettisonable nose sections of D-558 airplanes in two phases. The effects of center-of-gravity location and stabilizing fins of various sizes were also determined. The noses were found to tumble end over end at an approximately horizontal axis, which may be dangerous to the pilot if the nose is jettisoned while the airplane is traveling at a high rate of speed.
- High-Speed Stability and Control Characteristics of a Fighter Airplane Model with a Swept-Back Wing and Tail
- Memorandum presenting wind-tunnel tests conducted to determine the high-speed stability and control characteristics of an airplane model with a sweptback wing and tail. The aerodynamic coefficients and the longitudinal- and lateral-control characteristics of the plain wing-fuselage-tail combination are included. Results regarding lift, drag, and pitching moment, longitudinal characteristics, lateral characteristics, wing leading-edge slate, and fuselage-side dive brakes are provided.
- Experimental investigation of thrust augmentation of 4000-pound-thrust centrifugal-flow-type turbojet engine by injection of water and alcohol at compressor inlets
- Report presenting an experimental investigation at zero flight speed and sea-level conditions on a 4000-pound-thrust centrifugal-flow-type turbojet engine to determine the amount of thrust augmentation obtainable at maximum rotor speed by the injection of water, alcohol, and water-alcohol mixtures at the compressor inlets. A maximum thrust augmentation of 26 percent was obtained by the injection of 4.5 pounds per second of water and 2.0 pounds per second of alcohol. Results regarding the tail-pipe gas temperature, air-flow and compressor-outlet pressure, fuel flow, specific liquid consumption, and thrust augmentation are provided.
- The Effectiveness at High Speeds of a 10-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil Section
- This report contains the results of a high-speed wind-tunnel investigation of the effectiveness of a 10-percent-chord plain flap on the NACA 65-210 airfoil section. The results include an indication of the lift-producing characteristics and the effectiveness of the 10-percent-chord flap. From a comparison of the characteristics of the 10-percent-chord flap with those of a 20-percent-chord flap it was concluded that, although a reduction in flap-chord ratio from 0.20 to 0.10 lessens the severity of the effectiveness loss at supercritical speeds, the 20-percent-chord flap is more effective throughout the entire range of Mach numbers from 0.3 to 0.875.
- A fuel-distribution control for gas-turbine engines
- "The principle of operation of a device to control the distribution of fuel to any number of discharge nozzles of a gas-turbine engine is presented. A description of an experimental model of the device and the results of a bench investigation are presented. This device controlled the flow to four discharge nozzles within 2 percent of perfect distribution over a wide range of fuel flow and was unaffected by uneven discharge-nozzle pressures" (p. 1).
- Preliminary Results of Nene II Engine Altitude-Chamber Performance Investigation 2 - Altitude Performance Using 18.41-Inch Diameter-Jet Nozzle
- "An investigation is being conducted to determine the altitude performance characteristics of the Nene II engine and its components. The present paper presents preliminary results obtained using a jet nozzle of 18.41 inches in diameter, giving an area equal to 96.4 percent of the area of the standard jet nozzle of this engine. The test results presented are for conditions simulating altitudes from seal level to 50,000 feet and ram-pressure ratios from 1.00 to 2.70. The ram pressure ratios correspond to flight Mach numbers between zero and 1.28" (p. 1).
- Preliminary Investigation to Determine Propeller Section Characteristics by Measuring the Pressure Distribution on an NACA 10-(3)(08)-03 Propeller Under Operating Conditions
- "An investigation has been made in the Langley 16-foot high-speed tunnel to determine the propeller-section characteristics by measuring the pressure distribution on the airfoil sections of a rotating propeller. The pressures were measured at nine radial stations on an NACA 10-(3)(08)-03 design two-blade propeller. This paper presents the results of the pressure measurements in the form of normal-force and moment coefficients and covers a range of nominal angle of attack (simple blade element theory) from 0 degrees to 4 degrees for a section Mach number range of approximately 0.6 to 1.15 for the outboard stations and approximately 0.3 to 0.6 for inboard stations" (p. 1).
- High-Speed Wind-Tunnel Investigation of a Sweptback Wing With an Added Triangular Area at the Center
- Report discussing an investigation of two sweptback wings of different plan form in order to determine the effects of adding a triangular area to the inboard section of a conventional sweptback wing as a way to create a wing with two stages of sweepback. Lift, drag, and pitching-moment characteristics are provided for a range of Mach numbers.
- Investigation of a thin straight wing of aspect ratio 4 by the NACA wing-flow method: Lift and pitching-moment characteristics of the wing alone
- This report presents measurements of the lift and pitching-moment characteristics of a straight wing of aspect ratio 4, taper ratio 0.5, having a symmetrical double-wedge airfoil section with a maximum thickness of 4.4-percent chord. The tests were conducted in the Mach number range 0.51 to 1.20, Reynolds numbers 380,000 to 660,000, by the NACA wing-flow method. The results are compared with theory and with wind-tunnel tests of a similar model. It is indicated that in the Mach number range 0.82 to 1.00 the model surface, profile, and test Reynolds number all would be very important considerations in any attempt to study or predict full-scale characteristics from small-model tests.
- Effects of several leading-edge modifications on the stalling characteristics of a 45 degree swept-forward wing
- Report presenting an investigation to determine the effects of several leading-edge modifications on the maximum lift and pitching-moment characteristics on a large-scale 45 degree swept-forward wing. A full-span leading-edge flap deflected 30 degrees down tended to give the largest gain of maximum lift. Results regarding the plain leading-edge flaps and cambered nose are explored.
- A comparison of theoretical and experimental loading on a 63 degrees swept-back wing at supersonic speeds
- Report presenting the pressure distribution over a highly swept wing at supersonic speeds to provide data for a comparison of measured and predicted loadings. The wing for this investigation had 63 degrees of sweepback of the leading edge, an aspect ratio of 3.5, and a taper ratio of 0.25. Over the regions influenced by the wing tip and trailing edge, the effects of viscosity apparently are responsible for the poorer agreement between theory and experiment.
- The Effects of Horizontal-Tail Location and Wing Modifications on the High-Speed Stability and Control Characteristics of a 01.17-Scale Model of the McDonnell XF2H-1 Airplane (TED No, NACA DE336)
- "An additional series of high-speed wind-tunnel tests of a modified 0.17-scale model of the McDonnell XF2H-1 airplane was conducted to evaluate the effects of a reduction in the thickness-to-chord ratios of the tail planes, the displacement of the horizontal tail relative to the vertical tail, and the extension of the trailing edge of the wing. Two tail-intersection fairings designed to improve the flow at the tail were also tested. The pitching-moment characteristics of the model were improved slightly by the use of the thinner tail sections" (p. 1).
- An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 3: Characteristics of Wing With Body and Vertical Tail
- Report presenting an investigation to determine the aerodynamic characteristics in sideslip of a triangular wing of aspect ratio 2.04 in combination with a body of fineness ratio 12.5 and a vertical tail surface. The body combined with the triangular plan-form wing caused no significant changes in the lift characteristics of the wing and only a 1-percent decrease in the static margin. Results regarding the longitudinal characteristics, lateral and directional characteristics, and estimation of tail and rudder effectiveness are provided.
- Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio
- Report presenting a discussion of the aerodynamic forces and moments on inclined bodies of revolution. An approximate theory to allow for the effects of viscosity is developed and applied. Results regarding the variation of lift and pitching moment, and center of gravity are provided.
- Low-Speed Investigation of Deflectable Wing-Tip Ailerons on an Untapered 45 Degrees Sweptback Semispan Wing With and Without an End Plate
- Report presenting a low-speed wind-tunnel investigation to determine the characteristics of deflectable wing-tip ailerons on an untapered 45 degree sweptback semispan wing. Ailerons with triangular and parallelogram plan forms with a maximum chord of 0.625 wing chord and a flat-plat profile were investigated. The aerodynamic characteristics in pitch and lateral control characteristics are included.
- Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees
- Report presenting an investigation at subsonic and transonic speeds to determine the aerodynamic characteristics of three geometrically similar wings with 42 degree sweepback of the leading edge, aspect ratio 4, taper ratio 0.625, and NACA 64(sub)1-112 airfoils. The lift, drag, and pitching-moment characteristics are provided.
- Pressure Distributions on the Blade Sections of the NACA 10-(3)(049)-033 Propeller Under Operating Conditions
- A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.
- Stability and control characteristics at low speed of a 1/4-scale Bell X-5 airplane model: Longitudinal stability and control
- Report presenting an investigation of the low-speed longitudinal stability and control characteristics of a scale model of a Bell X-5 airplane design with various leading-edge slat and trailing-edge flap arrangements. A marked increase in stability with increasing sweep angle at low lift coefficients was noted. Results regarding the basic longitudinal characteristics, leading-edge slats, trailing-edge flaps, and longitudinal control are provided.
- Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Proposed by All American Airways, Inc.
- "At the request of the Air Materiel Command an investigation was made in the Langley free-flight tunnel to determine the static longitudinal stability and control characteristics of models coupled together in a tandem configuration proposed by All American Airways, Inc. Force tests were made using 1/20-scale models of B-29 end F-80 airplanes to determine the effects of coupling the fighter to the tail of the bomber. The results of the investigation showed that for the bomber alone the aerodynamic center was 0.21 mean aerodynamic chord behind the center of gravity (stable) but that for the tandem configuration the aerodynamic center was 0.09 mean aerodynamic chord forward of the center of gravity, of the combination (unstable)" (p. 1).
- An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Lateral Stability Characteristics at Mach Numbers of 1.40 and 1.59
- "An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel to determine the static lateral stability characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results of the investigation indicated high directional stability that decreased with increasing Mach number and positive effective dihedral that was essentially invariant with lift coefficient and Mach number" (p. 1).
- Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Several Combinations of the Tail With Each of Two Foreshortened Body Segments
- "An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone" (p. 1).
- Experimental and Analytical Study of Balanced-Diaphragm Fuel Distributors for Gas-Turbine Engines
- "A method of distributing fuel equally to a plurality of spray nozzles in a gas-turbine engine by means of balanced-diaphragm fuel distributors is presented. The experimental performance of three of eight possible distributor arrangements are discussed. An analysis of all eight arrangements is included. Criterions are given for choosing a fuel-distributor arrangement to meet specific fuel-system requirements of fuel-distribution accuracy, spray-nozzle pressure variations, and fuel-system pressures" (p. 1).
- Measurements of the effect of trailing-edge thickness on the zero-lift drag of thin low-aspect-ratio wings
- Report presenting an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models with tapered 4-percent-thick wings for a range of Mach numbers. Wings with an aspect ratio of 3.11 and trailing-edge thickness of 0, 1/3 maximum thickness, 2/3 maximum thickness, and 3/3 maximum thickness were tested.
- Penetration of Liquid Jets into a High-Velocity Air Stream
- Data are presented showing the penetration characteristics of liquid jets directed approximately perpendicular to a high-velocity air stream for jet-nozzle-throat diameters from 0.0135 to 0.0625 inch, air stream densities from 0.0805 to 0.1365 pound per cubic foot, liquid jet velocities from 168.1 to 229.0 feet per second and a liquid jet density of approximately 62 pounds per cubic foot. The data were analyzed and a correlation was developed that permitted the determination of the penetration length of the liquid jet for any operation condition within the range of variables investigated.
- Investigation of Downwash, Sidewash, and Mach Number Distribution Behind a Rectangular Wing at a Mach Number of 2.41
- "An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made" (p. 1).
- Effects of sweep on the damping-in-roll characteristics of three sweptback wings having an aspect ratio of 4 at transonic speeds
- Report presenting the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, an NACA 65A006 airfoil section, and three different sweep angles at a range of Mach numbers and angles of attack. The data were obtained in the 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique. Results regarding the damping-in-roll parameter, angle of attack, and lift-curve slope are provided.
- Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip
- Memorandum presenting an investigation conducted in the Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet with a conical spike and a supersonic cowl lip. Measurements of lift, drag, pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees.
- Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel
- "At the request of the Bureau of Aeronautics, Department of the Navy, an investigation of the Westinghouse XJ34-WE-32 turbojet engine is being conducted in the NACA Lewis altitude wind tunnel to determine the steady-state and transient operating characteristics of the controlled and uncontrolled engine at various altitudes and ram pressure ratios. As part of this program, transient performance data that illustrate the operation of the engine is obtained in the form of oscillographic traces. Similar data for engine operation in the afterburning range, covering a range of throttle settings from the minimum value giving rated speed (throttle position, 72 degrees) to full afterburning (throttle position, 110 degrees), is presented herein" (p. 1).
- Supersonic Tunnel Investigation by Means of Inclined-Plate Technique to Determine Performance of Several Nose Inlets Over Mach Number Range of 1.72 to 2.18
- Memorandum presenting a study using a suspended flat plate to continuously vary the Mach number in the 18- by 18-inch Mach number 1.91 supersonic tunnel. The technique was applied to the determination of pressure recovery and mass-flow characteristics of four supersonic nose inlets over the Mach number range produced. Results regarding the plate calibration and inlet performance are provided.
- Description and Investigation of a Dynamic Model of the XH-17 Two-Blade Jet Driven Helicopter
- Report presenting a description and results of an investigation of a model of the XH-17 two-blade, jet-powered helicopter. Tests were made with a standard configuration and with several modifications, including varying the size of blade counterweights, changing the control stiffness and chordwise bending stiffness of the blades, and varying the pylon and undercarriage damping and spring constants. Results regarding flutter testing, ground-vibration tests, and three-per-revolution rotor-blade unsymmetric bending oscillations are provided.
- Time Histories of the Aerodynamic Loads on the Vertical and Horizontal Tail Surfaces of a Jet-Powered Bomber Airplane During Sideslip Maneuvers at Approximately 20,000 Feet
- Report presenting time histories of the aerodynamic loads on the vertical and horizontal tail surfaces of a jet-powered bomber airplane (B-45A) in sideslip maneuvers. Information about maximum measured rudder and fin loads, maximum total vertical-tail load, horizontal-tail-load dissymmetry, maximum elevator loads, and elevator-load dissymmetry is provided.
- Wing-on and wing-off longitudinal characteristics of an airplane configuration having an thin unswept tapered wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4
- Report presenting flight tests at Mach numbers from 0.8 to 1.4 on three rocket-propelled general research models of airplane configurations. Two models had thin unswept tapered wings of aspect ratio 3 and hexagonal airfoil sections, two wings had different structural stiffness characteristics, and the third model had no wing. Results regarding the static and dynamic longitudinal stability, control, trim, and drag characteristics are provided.
- Note on flutter of a 60 degree delta wing encountered at low-supersonic speeds during the flight of a rocket-propelled model
- From Summary: "An analysis of the flight time history of a rocket-propelled model of a 60 degree delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented."
- Notes on Heat-Resistant Materials in Britain from Technical Mission October 13 to November 30, 1950
- Memorandum presenting a summary of heat-resistant materials obtained from interviews with alloy producers, jet-engine manufacturers, and research laboratories in Britain during October and November 1950. The primary subjects of interest included the properties of materials and service requirements for gas turbines, criteria used for judging and inspecting materials, and research developments of both a practical and fundamental nature in the field.
- Data presentation of force characteristics of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0
- Investigation to determine lift, drag, and pitching-moment characteristics of several engine-strut-body combinations was conducted over range of angles of attack from 0 degrees to 10 degrees at Mach numbers of 1.8 and 2.0. The average Reynolds number based on body length was 28x106. Data are presented without analysis and indicate decreases in minimum drag and lift curve slope with decreasing in minimum drag and lift curve slope with decreasing strut length. Decreases in minimum drag also noted with rear-ward movement of engines.