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- Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds
- Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
- Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1
- "An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability" (p. 1).
- 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.
- Full-Scale Wind-Tunnel Tests of a 35 Degree Swept-Wing Fighter Airplane With a Spoiler-Slot-Deflector Lateral Control System
- Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot deflector lateral control system installed ahead of the conventional ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the airplane and spoiler-slot-deflector effectiveness data were obtained through the complete angle-of-attack range with the ailerons neutral and with the ailerons drooped in conjunction with the normal flaps. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.
- 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.
- Pressure Distributions and Aerodynamic Characteristics of Several Spoiler-type Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01
- Memorandum presenting an investigation at Mach numbers of 1.61 and 2.01 to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results regarding pressure distributions, spanwise loadings, and integrated coefficients are provided.
- High-temperature oxidation and ignition of metals
- "A study of the high-temperature oxidation of several aircraft construction materials was undertaken to assess the possibility of ignition under high-temperature flight conditions.Tests have been made both in open and closed jets, and, in addition, the burning of metals has been observed under static conditions in a pressurized vessel containing either air, oxygen, or nitrogen. When heated in an atmosphere of oxygen or when heated and plunged into a supersonic airstream, titanium, iron, carbon steel, and common alloys such as 4130 were found to have spontaneous-ignition temperatures in the solid phase (below melting) and they melted rapidly while burning" (p. 1).
- A theoretical study of the lifting efficiency at supersonic speeds of wings utilizing indirect lift induced by vertical surfaces
- Report presenting a theoretical study of the possibility of improving the lifting efficiency of aircraft flying at supersonic speeds using indirect lift, which can be induced on the wing by the fuselage shape and/or wing end plates. Results indicated that lifting efficiency of a planar wing may be improved by favorable interference induced by lateral forces on the end plates or on the sides of the fuselage.
- External-stream effects on gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers
- Report presenting an investigation in the 8- by 6-foot supersonic tunnel to determine the external-stream effects on the gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers. Results regarding the pumping, thrust, and base characteristics, boattail drag characteristics, and stream effects on jet thrust for typical ejector installations are provided.
- Supersonic-Area-Rule Design and Rocket-Propelled Flight Investigation of a Zero-Lift Straight-Wing-Body-Nacelle Configuration Between Mach Numbers 0.8 and 1.53
- Memorandum presenting an application of the supersonic area rule concept to the deign of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. The pressure drag from the configuration with nacelles was found to be significantly less than that from a corresponding configuration without nacelles throughout the Mach number range.
- Full-scale wind-tunnel tests of a 35 degree swept-wing fighter airplane with a spoiler-slot-deflector lateral control system
- Report presenting an investigation to determine the low-speed aerodynamic characteristics of a 35 degree swept-wing fighter airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of conventional ailerons and operated as both individual units and combined segments. Results regarding longitudinal characteristics, spoiler-deflector characteristics, and hinge-moment characteristics are provided.
- Light Diffusion Through High-Speed Turbulent Boundary Layers
- Memorandum presenting the optical transmission characteristics of turbulent boundary layers in air on a flat plate with negligible heat transfer measured photometrically for ranges of Mach number from 0.4 to 2.5. The results indicated that the scattering from a collimated beam of white light which penetrates a turbulent boundary layer depends mainly on the integral across the layer of the difference between the free-stream density and the local boundary-layer density.
- Wind-Tunnel Investigation of a Ram-Jet Model Having a Wing and Canard Surfaces of Delta Plan Form With 70 Degrees Swept Leading Edges: Force and Moment Characteristics at Combined Angles of Pitch and Sideslip for Mach Number 2.01
- Results presenting an investigation in the supersonic pressure tunnel to determine the static stability and control characteristics of a ram-jet canard missile at Mach number 2.01. The missile had wings, canard surfaces of delta plan form with 70 degree swept leading edges, and two ram-jet nacelles. Results regarding the longitudinal and lateral characteristics are provided.
- Preliminary survey of compressor rotor-blade wakes and other flow phenomena with a hot-wire anemometer
- Report presenting the use of a hot-wire anemometer to study the tip-region flow phenomena at the exit of a single-stage transonic compressor rotor. The flow phenomena were recorded as a film which is available as a supplement to the report. Results regarding overall results of hot-wire measurements, quantitative results from hot-wire measurements, and some concluding remarks are provided.
- Application of area suction to leading-edge and trailing-edge flaps on a 44 degree swept-wing model
- From Introduction: "The results of tests in which area suction was applied near the leading edge of the wing or the knee of a leading-edge flap are reported in references 1 through 5."
- Wind-tunnel tests of blowing boundary-layer control with jet pressure ratios up to 9.5 on the trailing-edge flaps of a 35 degree sweptback wing airplane
- Report presenting a full-scale wind-tunnel investigation to determine whether the effects of blowing high-velocity air over trailing-edge flaps could be adequately correlated by jet momentum over a range of jet velocities. Good correlation of lift with jet momentum was obtained over the range of jet pressure ratios.
- Analysis of some parameters used in correlating blowing-type boundary-layer control data
- Report presenting an examination of the limitations of the use of jet momentum coefficient as a correlating factor in comparing tests of blowing-type boundary-layer control. Theoretical and experimental data indicate that it should be an acceptable parameter where the duct pressures are large.
- A Low-Speed Investigation of a High-Lift Lateral-Control Device Consisting of a Spoiler-Slot-Deflector and a Trailing-Edge Flap on a Tapered 45 Degree Sweptback Wing
- Report presenting an investigation to determine the aerodynamic characteristics of a spoiler-slot-deflector configuration in combination with a trailing-edge 29-percent-chord high-lift flap. The wing has a sweepback of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil. Results are also presented regarding the effect of deflector projection on the aerodynamic characteristics of a spoiler-slot-deflector on the plain wing.
- Investigation of unsteady flow past four NACA 6-percent-thick airfoil sections
- Report presenting an investigation of the intensity of root-mean-square pressure pulsations and root-mean-square normal-force-coefficient fluctuations conducted on two high-lift airfoils and two 6-series airfoils. Results regarding the factors affecting comparison of data from various test facilities, root-mean-square pressure pulsations, and root-mean-square force fluctuations are provided.
- Investigation of a 1/22-Scale Model 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 a model of the Republic F-105 in the transonic tunnel at a variety of Mach numbers. Results regarding lift characteristics, pitching-moment characteristics, zero-lift drag characteristics, maximum lift-drag ratio, flaperon and rudder characteristics, and effective downwash characteristics are provided.
- Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of plain spoilers on thin untapered wings at transonic speeds
- From Summary: "A wind-tunnel investigation has been made in the Langley high-speed 7- by 10-foot wind tunnel by use of the transonic-bump technique to study the effectiveness of spoiler-type controls on 9 unswept untapered wings. Full-span spoilers, projected to 7.5 percent wing chord along the 40-, 60-, 80-, and 100-percent wing chord lines, were tested on wings of aspect ratio 1 to 6 at Mach numbers from 0.6 to 1.10. Most of the data are presented without analysis."
- Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds
- Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio have been determined for Mach numbers of 1.97 and 3.33. The angle-of-attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. The results of the investigation indicate that there are distinct aerodynamic advantages to the use of highly swept wings of very low aspect ratio.
- Measurements of Boundary-Layer Transition at Low Speed on Two Bodies of Revolution in a Low-Turbulence Wind Tunnel
- Memorandum presenting an investigation of the location of transition from laminar to turbulent flow in the boundary layer on two bodies of revolution at zero angle of attack in a low-turbulence wind tunnel. One body was a prolate spheroid of fineness ratio 9.0 made out of aluminum and the other was a modified prolate spheroid of fineness ratio 7.5 made out of steel and covered with fiberglass and resin.
- Flight Tests of Fifteen T-231 Gun-Launched Rocket Projectiles
- "Flight tests of fifteen T-231 70-mm HEAA rocket projectiles (flight components of the T-263 HEAA rounds) were made at the Langley Pilotless AIrcraft Research Station at Wallops Island, VA., to obtain flight trajectories at high quadrant elevation launchings and to obtain drag data. Although all rounds were of the same general type, there were differences in nozzle cant angles, number of nozzles per round, shape of head and fuse, motor case length, and type of propellant. All projectiles were launched at an elevation angle of 60 deg" (p. 1).
- Effect of Ambient Conditions on the Performance of a Pressure-Jet Powerplant for a Helicopter
- Memorandum presenting a generalized analysis of a pressure-jet powerplant. The effect of changes in ambient conditions on the powerplant performance is provided in a series of charts using parameters containing temperatures and pressures. Some of the variables investigated included the pressure-jet powerplant performance in helicopter and pressure-jet-helicopter performance.
- Free-flight investigation of the control effectiveness of a differentially deflected horizontal tail at Mach numbers from 0.8 to 1.6
- Report presenting a free-flight investigation of the control effectiveness of a differentially deflected horizontal tail. The results were compared with and found to be in general agreement with estimates derived from other free-flight tests, wind tunnel tests, and theory. Results regarding the rolling moment, yawing moment, and overall rolling effectiveness are provided.
- Injection principles for liquid oxygen and heptane using two-element injectors
- Report presenting a study of injection principles for liquid oxygen and heptane made with two-element injectors, as the previous study only included single-element injectors. Eight injectors, produced by two spray orientations of each of the four injection processes, were investigated. Results regarding atomization after mixing, atomization before mixing, atomization without mixing, fuel atomization without mixing, and overall comparisons of the injectors are provided.
- Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0
- Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.
- Experimental Transonic Flutter Characteristics of an Untapered, 45 Degree Sweptback, Aspect Ratio 4 Wing
- Report presenting the flutter characteristics of an untapered, 45 degree sweptback, aspect-ratio-4 wing at a range of Mach numbers. The results from NACA RM L55E19a are included along with additional information regarding the models, the tests, and the results of the flutter calculations.
- Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9
- Report presenting measurements of aerodynamic heat transfer at six stations on the 40-inch-long 10 degree total-angle conical nose of a rocket-propelled model at Mach numbers up to 5.9. Laminar, transitional, and turbulent heat-transfer coefficients were obtained for Mach numbers up to 4. Results regarding skin temperature time histories, boundary-layer transition, and calculated skin temperature are provided.
- Investigation at high subsonic speeds of some effects of sideslip on the aerodynamic loads on finned and unfinned bodies mounted from the wing of a swept-wing-fuselage model
- Report presenting an investigation in the high-speed 7- by 10-foot tunnel at a range of Mach numbers to determine the aerodynamic loads on finned and unfinned bodies in the presence of a swept wing. A tip-mounted body at 1.04 semispan and an underwing pylon-mounted body at 0.33 semispan were investigated. Results regarding the body loading characteristics and effect of angle of attack are provided.
- A preliminary investigation of the static stability characteristics of four airplane-like configurations at Mach numbers from 3.00 to 6.28
- Report presenting side-force and directional-stability characteristics of four airplane-like configurations determined at a range of Mach numbers and angles of sideslip at zero angle of attack. Two configurations had trapezoidal wing and tail surfaces and two had triangular wing and tail surfaces. The directional stability of the configurations generally decreased with increasing Mach number.
- Investigation of the Ejection Release of Several Dynamically Scaled Bluff Internal Stores at Mach Numbers of 0.8, 1.39, and 1.98
- Report presenting an investigation to determine flight behavior after ejection from a bomb bay of several dynamically scaled bluff internal stores for a range of Mach numbers and altitudes. The trajectories of all of the stores were smooth, but the pitching motions of the stores were greatly affected by the close vicinity of the bomb bay. Types of stores explored included WADC stores, flared-cylinder stores, and cylindrical stores.
- Experimental Study and Analysis of Loading and Pressure Distributions on Delta Wings Due to Thickness and to Angle of Attack at Supersonic Speeds
- Memorandum presenting the aerodynamic loading on delta wings at supersonic speeds, which was studied primarily to determine the coupling and nonlinear interference effects between the pressures due to angle of attack and due to thickness. Results regarding span loadings and lift coefficients, pressure distributions due to thickness, pressure distributions due to angle of attack and interference pressures produced by thickness, and Reynolds number effects are provided.
- 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
- Memorandum presenting an investigation in the 27- by 27-inch preflight jet on the release characteristics of several dynamically scaled store shapes from a simulated bomb bay at Mach numbers of 1.30, 1.60, and 1.98. A model of a typical fighter-bomber airplane with high sweptback wings was used. Results for streamline store A, blunt-nose store B, and bluff store C are provided.
- Wind-tunnel investigation of the damping in roll of the Bell X-1E research airplane and its components at supersonic speeds
- Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided.
- Pressure distributions and aerodynamic characteristics of several spoiler-type controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01
- Report presenting an investigation at two Mach numbers to examine the characteristics of a series of nine spoiler-type controls on a trapezoidal wing with the leading edge swept back 23 degrees, an aspect ratio of 3.1, and a taper ratio of 0.4. Results of the tests indicated that the incremental pressure distributions due to spoiler were in agreement with previous results as long as the spoiler was not too close to a break in the wing surface or the wing tip.
- Zero-Lift Drag of a Series of Bomb Shapes at Mach Numbers From 0.60 to 1.10
- Report presenting zero-lift drag data obtained on a series of six bomb shapes. Five configurations had the same body shape with different body-surface conditions and profile and plan form of fins, and the sixth had a different and longer body shape. Results regarding the effect of blunt trailing edge, blunt leading edge, fin thickness, and body surface are provided.
- Stability of Systems Containing a Heat Source - The Rayleigh Criterion
- "The stability of systems containing a heat source is examined from the energy point of view. Rayleigh's criterion is derived. In the case of a flame, it is found that Rayleigh's criterion must be modified slightly if the specific-heat ratios of the burned and unburned gases are different" (p. 1).
- ESTIMATION OF ATHEROGENIC INDEX AND ACCUMULATED CORONARY DISEASE IN HUMAN MALES: EVALUATION FROM SERUM GRAVIMETRIC "TOTAL LIPID" OR TOTAL CHOLESTEROL CONCENTRATION
- No Description Available.
- Health physics regional monitoring semiannual report, July--December 1955
- No Description Available.
- DIFFERENTIAL INFRARED ABSORPTION TECHNIQUES FOR CHARACTERIZING THE SURFACE OF ThO$sub 2$
- No Description Available.
- TWO TUBE STEAM EVAPORATOR NO. 3. Technical Report No. 51
- No Description Available.
- Internal Recombination in the HRR
- No Description Available.
- Light Isotopes of Berkelium and Californium
- No Description Available.
- The Relationship Between Surface Grade and Depth of Damage of Burns Produced by Radiant Thermal Energy
- No Description Available.
- Permissible Fuel Concentration in the Dump Tank of the Homogeneous Research Reactor
- No Description Available.
- RECOVERY AND PURIFICATION OF URANIUM BY CONTINUOUS ION EXCHANGE AND ELECTROLYSIS
- No Description Available.
- HAYNES ALLOY 25 SPRING MATERIAL
- No Description Available.
- Emergency Shutdown of the Appr-1 by Poisoning With Boron
- No Description Available.