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Flight Instrument for Measurement of Liquid-Water Content in Clouds at Temperatures Above and Below Freezing

Description: "A principle formerly used in an instrument for cloud detection was further investigated to provide a simple and rapid means for measuring the liquid-water content of clouds at temperatures above and below freezing. The instrument consists of a small cylindrical element so operated at high surface temperatures that the impingement of cloud droplets creates a significant drop in the surface temperature. The instrument is sensitive to a wide range of liquid-water content and was calibrated at one… more
Date: March 6, 1951
Creator: Perkins, Porter J.
Partner: UNT Libraries Government Documents Department
open access

Meteorological Analysis of Icing Conditions Encountered in Low-Altitude Stratiform Clouds

Description: "Liquid-water content, droplet size, and temperature data measured during 22 flights in predominately stratiform clouds through the 1948-49 and the 1949-50 winters are presented. Several icing encounters were of greater severity than those previously measured over the same geographical area, but were within the limits of similar measurements obtained over different terrain within the United States. An analysis of meteorological conditions existing during the 74 flights conducted for four winter… more
Date: March 1951
Creator: Kline, Dwight B. & Walker, Joseph A.
Partner: UNT Libraries Government Documents Department
open access

A General Through-Flow Theory of Fluid Flow With Subsonic or Supersonic Velocity in Turbomachines of Arbitrary Hub and Casing Shapes

Description: Note presenting a general steady through-flow theory of nonviscous fluid in turbomachines of arbitrary hub- and casing-wall shapes with subsonic or supersonic velocity. The theory is applicable to both direct and inverse problems and is derived primarily for use in turbomachines with thin blades of high solidity with a simple approximate correction factor for blade-thickness effect.
Date: March 1951
Creator: Wu, Chung-Hua
Partner: UNT Libraries Government Documents Department
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Three-Dimensional Compressible Laminar Boundary-Layer Flow

Description: Note presenting the equations governing the three-dimensional compressible laminar boundary layer with variable viscosity and thermal conductivity, which are shown to be simplified by the introduction of a two-component vector potential, the use of a transformation to change the equations into nearly incompressible form, and the use of a further transformation that changes the equations into nearly Cartesian form when a coordinate system appropriate to axial or conical symmetry is used. Problem… more
Date: March 1951
Creator: Moore, Franklin K.
Partner: UNT Libraries Government Documents Department
open access

The use of an uncalibrated cone for determination of flow angles and Mach numbers at supersonic speeds

Description: Report presenting a pressure-distribution investigation of a body of revolution in the 4- by 4-foot supersonic tunnel at a Mach number of 1.59. Results regarding the basic pressure-distribution data, reduction of conical-pitot-yaw-head data, four-static orifice system, flow-angle determination, other orifice systems, and general comments on theoretical prediction of pressure distribution on cone surfaces are provided.
Date: March 1951
Creator: Cooper, Morton & Webster, Robert A.
Partner: UNT Libraries Government Documents Department
open access

A Method for the Determination of the Spanwise Load Distribution of a Flexible Swept Wing at Subsonic Speeds

Description: Note presenting a method for the determination of the spanwise load distribution of a flexible swept wing at subsonic speeds. The method is based on a relaxation approach using aerodynamic loadings obtained from previously published work based on Weissinger's simplified lifting-surface theory together with simple beam theory.
Date: March 1951
Creator: Skoog, Richard B. & Brown, Harvey H.
Partner: UNT Libraries Government Documents Department
open access

Vibratory stresses in propellers operating in the flow field of a wing-nacelle-fuselage combination

Description: Report presenting an investigation to determine the first-order vibratory stresses induced in propellers of conventional design when rotating in the flow field of a wing-nacelle-fuselage combination, which also enables an evaluation of the steps essential to the prediction of the stresses. Thrust measurements were obtained by means of propeller-wake surveys in order to define the magnitude of the force changes experienced by the blades. Results regarding the oscillating air loads and vibratory … more
Date: March 1951
Creator: Rogallo, Vernon L.; Roberts, John C. & Oldaker, Merritt R.
Partner: UNT Libraries Government Documents Department
open access

Charts for estimation of longitudinal-stability derivatives for a helicopter rotor in forward flight

Description: Report presenting charts to provide a convenient means for obtaining the derivatives of rotor resultant force, rotor pitching amount about the helicopter center of gravity, and rotor torque with respect to rotor angle of attack, forward speed, rotor speed, and collective pitch.
Date: March 1951
Creator: Amer, Kenneth B. & Gustafson, Frederic Bowen
Partner: UNT Libraries Government Documents Department
open access

Full-Scale-Tunnel Investigation of the Static-Thrust Performance of a Coaxial Helicopter Rotor

Description: Note presenting an investigation to determine the static-thrust performance of a coaxial helicopter rotor with blades tapered both in plan form and thickness ratio in the full-scale tunnel. Tests of the coaxial-rotor and single-rotor configurations were made for a range of blade-pitch setting and for a range of tip speed up to 500 feet per second. Results regarding the hovering performance, effect of variation in directional control, and variation of rotor figure of merit with ratio of thrust c… more
Date: March 1951
Creator: Harrington, Robert D.
Partner: UNT Libraries Government Documents Department
open access

Fatigue strengths of aircraft materials: axial load fatigue tests on unnotched sheet specimens of 24S-T3 and 75S-T6 aluminum alloys and of SAE 4130 steel

Description: Report presenting information on the axial-load fatigue behavior of unnotched specimens of 24S-T3 and 75S-T6 aluminum alloys and normalized SAE 4130 steel. The primary objectives of the investigation were to determine fatigue strengths and measurements of damage due to stress level are provided. Results regarding static strength tests, fatigue strength tests, fatigue damage tests, and results at high and low speeds are provided.
Date: March 1951
Creator: Grover, H. J.; Bishop, S. M. & Jackson, L. R.
Partner: UNT Libraries Government Documents Department
open access

Generalized Linearized Conical Flow

Description: Note presenting a basic theory of generalized linearized supersonic conical flow for both inside and outside the Mach cone, which was developed and applied to several specific problems including unsteady-flow conditions. A triangular lifting wing in pitching and rolling with both subsonic and supersonic leading edges was investigated and pressure coefficients were obtained.
Date: March 1951
Creator: Hayes, W. D.; Roberts, R. C. & Haaser, N.
Partner: UNT Libraries Government Documents Department
open access

Some properties of beryllium oxide and beryllium oxide - columbium ceramals

Description: High-temperature tensile and thermal-shock investigations were conducted on beryllium oxide and beryllium oxide plus columbium metal additions. X-ray diffraction and metallographic results are given. The tensile strength of 6150 pounds per square inch for beryllium oxide at 1800 degrees F compared favorably with the zirconia bodies previously tested. Additions of 2, 5, 8, 10, 12, and 15 percent by weight of columbium metal failed to improve the shock resistance over that of pure beryllium oxide. more
Date: March 2, 1951
Creator: Robards, C. F. & Gangler, J. J.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation at Mach Numbers From 0.8 to 1.5 of the Drag of a Canopy Located at Two Positions on a Parabolic Body of Revolution

Description: Report presenting the results of a free-flight investigation of two drag research models equipped with canopies for a range of Mach numbers from 0.8 to 1.5. The main difference between the models was the location of the canopy, which was at the 15-percent fuselage station on one model and the 25-percent fuselage station on the other. The additional drag due to the canopies was about 10 to 20 percent of the total configuration drag at supersonic speeds.
Date: March 15, 1951
Creator: Welsh, Clement J. & Morrow, John D.
Partner: UNT Libraries Government Documents Department
open access

Langley 9-Inch Supersonic Tunnel Tests of Several Modifications of a Supersonic Missile Having Tandem Cruciform Lifting Surfaces: Three-Component Data Results of Models Having Ratios of Wing Span to Tail Span Equal to 1

Description: Memorandum presenting tests in the 9-inch supersonic tunnel to investigate the factors that determine the magnitude of the wing-tail interference effects on the static longitudinal stability of supersonic missile configurations with low-aspect-ratio, tandem, cruciform lifting surfaces and to develop a missile configuration with a minimum variation in static margin due to wing-tail interference effects.
Date: March 7, 1951
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department
open access

A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2: Wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai

Description: Report presenting an analysis of a series of wing-body combinations in the 8-foot high-speed tunnel. The paper presents the results of an investigation of a wing-fuselage combination with a wing of unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Results regarding force and moment characteristics and wake and downwash characteristics are provided.
Date: March 6, 1951
Creator: Cahn, Maurice S. & Bryan, Carroll R.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Mass Distribution on the Low-Speed Dynamic Lateral Stability and Control Characteristics of a Model With a 60 Degree Triangular Wing

Description: Memorandum presenting an investigation to determine the effect of mass distribution on the dynamic lateral stability and control characteristics of a model with a 60 degree triangular wing in the free-flight tunnel. Flight tests and calculations were made for five different loading conditions. Results regarding the oscillatory stability, lateral control, and general flight behavior are provided.
Date: March 9, 1951
Creator: Johnson, Joseph L.
Partner: UNT Libraries Government Documents Department
open access

Damping in a roll of a missile configuration with a modified triangular wing and a cruciform tail at a Mach number of 1.52

Description: Report presenting the damping-in-roll stability derivatives of a missile configuration and its components as determined experimentally and theoretically. The experimental damping derivative of the wing-body combination was found to be 67 percent of its theoretical value. Results are given for the wing-body combination, the tail-body combination, and the wing-tail-body combination.
Date: March 6, 1951
Creator: Scherrer, Richard & Dennis, David H.
Partner: UNT Libraries Government Documents Department
open access

Large-scale flight measurements of zero-lift drag at Mach numbers from 0.8 to 1.6 of a wing-body combination having an unswept 4.5 percent thick wing with modified hexagonal sections

Description: Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination from high-subsonic to supersonic speeds in a range of Reynolds numbers. The wing was unswept about the 74.5-percent-chord line, an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections. Results regarding total drag, wing-plus-interference drag, and base pressure are provided.
Date: March 23, 1951
Creator: Schult, Eugene D.
Partner: UNT Libraries Government Documents Department
open access

Skin-Temperature Telemeter for Determining Boundary-Layer Heat-Transfer Coefficients

Description: Memorandum presenting a description of a method of telemetering skin temperature using a small resistance wire pickup with a time constant of less than 0.003 second to determine boundary-layer heat-transfer coefficients. An evaluation of the accuracy of the method of measuring the heat-transfer coefficient is given for a particular application.
Date: March 15, 1951
Creator: Fricke, Clifford L. & Smith, Francis B.
Partner: UNT Libraries Government Documents Department
open access

Notes on low-lift buffeting and wing dropping at Mach numbers near 1

Description: From Summary: "A study of the available transonic Mach number data on low-lift buffeting, wing dropping, and changes in the angles of zero lift for symmetrical airfoils indicates that these phenomena are allied and are probably the result of shock-induced separation. The study has indicated that there are combinations of airfoil-thickness ratio, aspect ratio, and sweep which may allow flight through the transonic speed range without experiencing buffet or wing drop at low lift."
Date: March 16, 1951
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department
open access

Combustion properties of aluminum as ram-jet fuel

Description: Report presenting an experimental investigation to determine the combustion properties of aluminum as a fuel for use in high-speed aircraft. The aluminum fuel was injected both in powder and wire form into 2-inch-diameter ramjet-type combustors. Results regarding operational problems, thrust, and combustion efficiency are provided.
Date: March 28, 1951
Creator: Branstetter, J. Robert; Lord, Albert M. & Gerstein, Melvin
Partner: UNT Libraries Government Documents Department
open access

Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers From 1.59 to 1.99 4: Conical-Spike External-Internal Compression Inlet Utilizing Perforated Cowl

Description: Report presenting testing conducted to determine the force and pressure-recovery characteristics of a model utilizing a single-shock spike-type inlet with a perforated cowl. The use of the cowl resulted in the attainment of a high pressure recovery at zero angle of attack, but it was accompanied by a relatively large increase in external drag as compared with nonperforated inlets of the same proportions. Results regarding the characteristics at zero angle of attack, effects of changes in angle … more
Date: March 28, 1951
Creator: Madden, Robert T. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department
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