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An Investigation of the Dynamic and Static Stability Characteristics of a Group of Specialized Store Configurations at Transonic Speeds

Description: Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date: August 21, 1953
Creator: Henry, Beverly Z., Jr. & Braden, John A.
Partner: UNT Libraries Government Documents Department
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Development of a Supersonic Area Rule and an Application to the Design of a Wing-Body Combination Having High Lift-to-Drag Ratios

Description: Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.
Date: August 18, 1953
Creator: Whitcomb, Richard T. & Fischetti, Thomas L.
Partner: UNT Libraries Government Documents Department
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Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner

Description: "Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner a… more
Date: August 6, 1953
Creator: von Glahn, U.
Partner: UNT Libraries Government Documents Department
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Measurement and Analysis of Turbulent Flow Containing Periodic Flow Fluctuations

Description: Memorandum presenting techniques for the measurement of the energy spectrum of flow fluctuations in both axial and lateral flow directions. A simple spectrum analysis is presented by which quantitative distinction may be made between turbulence and the flow disturbances associated with sound waves in ducts. Results regarding the measurement and analysis of turbulent-flow fields containing random and periodic flow fluctuations, effect of random sound disturbances on turbulence spectrum, and effe… more
Date: August 19, 1953
Creator: Mickelsen, William R. & Laurence, James C.
Partner: UNT Libraries Government Documents Department
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Rocket Engine Starting With Mixed Oxides of Nitrogen and Liquid Ammonia by Flow-Line Additives

Description: Memorandum presenting an investigation of the starting characteristics of mixed oxides of nitrogen - liquid ammonia rocket engines with light metal additives in the ammonia flow line for ignition. The oxidant consisted of 70 percent by weight nitrogen tetroxide and 30 percent nitric oxide. Results regarding the ignition experiments with 100-pound-thrust engine, 1000-pound-thrust engine experiments, and low-temperature experiments are provided.
Date: August 19, 1953
Creator: Kinney, George R.; Humphrey, Jack C. & Hennings, Glen
Partner: UNT Libraries Government Documents Department
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A flight investigation of the effect of steady rolling on the natural frequencies of a body-tail combination

Description: Report presenting flight experiments with a freely falling model to observe the effects of steady rolling on the pitching and yawing motions of a body-tail combination. Steady rolling introduces yawing moments into the pitch oscillations and pitching motions into the yaw oscillations. Results regarding the experimental effects of steady-roll on no-roll natural frequencies, comparison of measured and experimental effects of steady rolling on the no-roll natural frequencies, and effects of roll a… more
Date: August 1953
Creator: Bergrun, Norman R. & Nickel, Paul A.
Partner: UNT Libraries Government Documents Department
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Effect of blade-thickness taper on axial-velocity distribution at the leading edge of an entrance rotor-blade row with axial inlet, and the influence of this distribution on alignment of the rotor blade for zero angle of attack

Description: Report presenting a method for estimating the effect of blade-thickness taper on the inlet axial-velocity distribution of an entrance rotor-blade row with an axial inlet, and the influence of this velocity distribution on the alignment of the rotor blade for zero effective angle of attack. The method is developed for compressible and incompressible nonviscous fluids, and results are presented for incompressible flow into a plane, two dimensional cascade and for compressible flow into an entranc… more
Date: August 1953
Creator: Stanitz, John D.
Partner: UNT Libraries Government Documents Department
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An analysis of the power-off landing maneuver in terms of the capabilities of the pilot and the aerodynamic characteristics of the airplane

Description: From Introduction: "In the present paper, an analysis of the power-off landing maneuver is presented in which an attempt is made to consider both the aerodynamic characteristics of the airplane and the human capabilities of the pilot. In this paper, the type of pilot judgment considered is that of a pilot with previous flight experience, although not necessarily flight experience in any particular airplane under discussion."
Date: August 1953
Creator: von Doenhoff, Albert E. & Jones, George W., Jr.
Partner: UNT Libraries Government Documents Department
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Studies of the use of Freon-12 as a wind tunnel testing medium

Description: Report presenting a comparison of studies relating to the use of Freon-12 as a substitute medium for air in aerodynamic testing and methods for predicting the aerodynamic characteristics of bodies in air. The Freon charging and recovery system for the Langley low-turbulence pressure tunnel is described.
Date: August 1953
Creator: von Doenhoff, Albert E.; Braslow, Albert L. & Schwartzberg, Milton A.
Partner: UNT Libraries Government Documents Department
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Column Strength of H-Sections and Square Tubes in Postbuckling Range of Component Plates

Description: Note presenting a calculation of the column buckling stress in the range where the component plates have buckled using the method of split rigidities. Tests were carried out for a considerable range of slenderness ratios on three H-sections and two square tube sections.
Date: August 1953
Creator: Bijlaard, P. P. & Fisher, G. P.
Partner: UNT Libraries Government Documents Department
open access

Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Description: From Introduction: "Light-airplane accident data, compiled by Crash Injury Research of Cornell University Medical College, indicate that human beings have often withstood declarations in excess of those imposed in airplane crashes involving extensive damage to the airplane structure (ref. 1). This study also correlates the extent of damage to the airplane structure with the injury incurred by the occupants during crash accidents."
Date: August 1953
Creator: Eiband, A. Martin; Simpkinson, Scott H. & Black, Dugald O.
Partner: UNT Libraries Government Documents Department
open access

Application of a characteristic blade-to-blade solution to flow in a supersonic rotor with varying stream-filament thickness

Description: From Introduction: "A solution of the type of reference 2 is necessary to give the stream-sheet thickness and curvature for the blade-to-blade (S1 surface) solution considered in this report. The equations for the solution of the S1 surface of revolution are presented in reference 3. The purpose of the subject report is to continue the work of reference 3 by applying the method to a specific problem in order that the practicability of the method and the time involved in computing a solution may… more
Date: August 1953
Creator: Costilow, Eleanor L.
Partner: UNT Libraries Government Documents Department
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An analysis of normal-acceleration and airspeed data from a four-engine type of transport airplane in commercial operation on an eastern united states route from November 1947 to February 1950

Description: Report presenting an analysis of 48,187 hours of normal-acceleration and airspeed data obtained on a four-engine type of transport airplane in commercial operation on an eastern United States route from November 1947 to February 1950 to determine gusts and gust loads for operations. Results regarding the presentation of data, effect of changes in operating conditions, effect of seasons, comparison with other results, reliability, acceleration, gusts, and airspeeds are provided.
Date: August 1953
Creator: Coleman, Thomas L. & Schumacher, Paul W. J.
Partner: UNT Libraries Government Documents Department
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Charts Relating the Compressive Buckling Stress of Longitudinally Supported Plates to the Effective Deflectional and Rotational Stiffness of the Supports

Description: Report presenting a stability analysis of a long flat rectangular plate subjected to uniform longitudinal compressive stress and support along its longitudinal edges and one or more other longitudinal lines by elastic line supports. This was performed in order to provide more information about stabilization methods for thin-wing construction. The effective stiffness of different supports and the buckling observed in different structures is provided.
Date: August 1953
Creator: Anderson, Roger A. & Semonian, Joseph W.
Partner: UNT Libraries Government Documents Department
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Flight measurements and analysis of helicopter normal load factors in maneuvers

Description: Report presenting flight testing in two single-rotor helicopters to determine the load factors due to maneuvers. Additional information has also been obtained from military pilot training and commercial air-mail operations with helicopters. Results regarding the means of attaining maximum flight loads, predictability of load factors, and design limit load factors are provided.
Date: August 1953
Creator: Gustafson, F. B. & Crim, Almer D.
Partner: UNT Libraries Government Documents Department
open access

The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction

Description: Report presenting an investigation to study the aerodynamic characteristics of an aspect-ratio-20 wing with thick airfoil sections and employing boundary-layer control by suction. The results include the effects of varying suction flow rate, suction-slot configuration, wing surface condition, flap deflection, and Mach number are provided.
Date: August 1953
Creator: Cocke, Bennie W., Jr.; Fink, Marvin P. & Gottlieb, Stanley M.
Partner: UNT Libraries Government Documents Department
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A Study of the Stability of the Incompressible Laminar Boundary Layer on Infinite Wedges

Description: Note presenting a theoretical investigation of the flow over infinite wedges to test a conclusion that in a region of falling pressure, a thick velocity profile can be more stable than a thin profile although the velocity at the edge of the boundary layer and the pressure gradient are the same for both profiles. The investigation also leads to the interference that the calculated effects of a change in boundary-layer thickness on the stability and on the local roughness Reynolds number should b… more
Date: August 1953
Creator: Tetervin, Neal
Partner: UNT Libraries Government Documents Department
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A note on secondary flow in rotating radial channels

Description: "A general vector differential equation for the vorticity component parallel to a streamline is derived for steady, nonviscous, and incompressible flow in a rotating system. This equation is then simplified by restricting it to rotating radial channels and by making further simplifying assumptions. The simplified equation is used to solve for the secondary vorticity, the vorticity component parallel to the streamline, in three special cases involving different streamtube geometries; the results… more
Date: August 31, 1953
Creator: Kramer, James J. & Stanitz, John D.
Partner: UNT Libraries Government Documents Department
open access

Lateral Oscillatory Characteristics of the Republic F-91 Airplane Calculated by Using Low-Speed Experimental Static and Rotary Derivatives

Description: From Summary: "The present investigation was conducted to determine, from low-speed tests in the Langley stability tunnel, the static and rotary derivatives of a 1/9-scale model of the Republic F-91 airplane and various of its components (including the effects of wing incidence) and to determine the accuracy with which the period and damping of the lateral oscillation of the airplane could be calculated by using these experimentally between flight and calculated period and damping of the latera… more
Date: August 21, 1953
Creator: Jaquet, Byron M. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department
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Investigation of the Spinning and Tumbling Characteristics of a 1/25-Scale Model of the Lockheed XFV-1 Airplane in the Langley 20-Foot Free-Spinning Tunnel

Description: "An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/23-scale model of the Lockheed XFV-1 airplane to determine the effects of control setting and movement upon the erect-spin and recovery characteristics for a range of airplane loading conditions. A windmilling propeller was simulated on the model for some of the tests. The investigation included determination of the size of tail parachute required for emergency recovery from demonstration spins" (p. 1).
Date: August 21, 1953
Creator: Lee, Henry A.
Partner: UNT Libraries Government Documents Department
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A Study of the Motion and Aerodynamic Heating of Missiles Entering the Earth's Atmosphere at High Supersonic Speeds

Description: From Summary: "A simplified analysis is made of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds. It is found that, in general, the gravity force is negligible compared to the aerodynamic drag force and, hence, that the trajectory is essentially a straight line. A constant drag coefficient and an exponential variation of density with altitude are assumed and generalized curves for the variation of missile speed and deceleration with alt… more
Date: August 25, 1953
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Partner: UNT Libraries Government Documents Department
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Preliminary Appraisal of Ferrocene as an Igniting Agent for JP-4 Fuel and Fuming Nitric Acid

Description: From Summary: "A preliminary experimental study was made of the properties of ferrocene as a solute and as a suspension in JP-4 fuel, and of the ignition delays of ferrocene - JP-4 mixture with A.F. specification 14104 white fuming nitric acid (WFNA). The investigation covered concentrations of 4 to 10 percent by weight ferrocene, and a temperature range of -40 to 80 F. The solubility of ferrocene in JP-4 is about 5 percent at room temperature and about 1 percent (extrapolated) at -80 F. The so… more
Date: August 25, 1953
Creator: Miller, Riley O.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Description: "An investigation has been made at high subsonic speeds of the aerodynamic characteristics in pitch and sideslip of a 1/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for s… more
Date: August 18, 1953
Creator: Kuhn, Richard E. & Draper, John W.
Partner: UNT Libraries Government Documents Department
open access

Altitude Wind Tunnel Investigation of the Prototype J40-WE-8 Turbojet Engine Without Afterburner

Description: From Introduction: "As part of a comprehensive investigation of the J40 turbojet engine conducted at the NACA Lewis altitude wind tunnel, the steady-state engine performance of the prototype J40-WE-8 turbojet engine without afterburner was obtained and is presented herein. A basic redesign of the compressor and other modifications in the compressor and the combustor were incorporated in the XJ40-WE-6 turbojet engine (references 2 and 3). In this report the modified engine is designated "the pro… more
Date: August 6, 1953
Creator: McAulay, John E. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department
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