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The 6-Foot-4-Inch Wind Tunnel at the Washington Navy Yard
Report discussing the 6-foot-4-inch wind tunnel and its auxiliary equipment has proven itself capable of continuous and reliable output of data. The real value of the tunnel will increase as experience is gained in checking the observed tunnel performance against full-scale performance. Such has been the case of the 8- by 8-foot tunnel, and for that reason the comparison in the calibration tests have been presented.
Date:
August 1935
Creator:
Desmond, G. L. & McCrary, J. A.
System:
The UNT Digital Library
Accelerations and passenger harness loads measured in full-scale light-airplane crashes
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.
System:
The UNT Digital Library
Accuracy of Approximate Methods for Predicting Pressures on Pointed Nonlifting Bodies of Revolution in Supersonic Flow
Note presenting an investigation of the accuracy and range of applicability of the linearized theory, second-order theory, tangent-cone method, conical-shock-expansion theory, and Newtonian theory for predicting pressure distributions on pointed bodies of revolution at zero angle of attack. Three shapes, cone, ogive, and a modified optimum body, are investigated over a wide range of fineness ratios and Mach numbers. The results indicated that for most combinations of fineness ratio and Mach number, one of the approximate methods will give reasonable results.
Date:
August 1952
Creator:
Ehret, Dorris M.
System:
The UNT Digital Library
Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces
From Introduction: "The experiments in high-speed flow showed that an intense, high-frequency acoustic radiation is an essential feature of the problem. Consequently, a study of the acoustic field (involving schlieren observations and frequency and intensity measurements) was undertaken. This report presents the salient features of the study, which was mainly exploratory."
Date:
August 1955
Creator:
Krishnamurty, K.
System:
The UNT Digital Library
Adhesion of Ice in Its Relation to the De-Icing of Airplanes
From Summary: "The various possible means of preventing ice adhesion on airplane surfaces are critically reviewed. Results are presented of tests of the adhesives forces between ice and various solid and liquid forces. It is concluded that the de-icing of airplane wings by heat from engine exhaust shows sufficient promise to warrant full-scale tests. For propellers, at least, and possibly for certain small areas such as windshields, radio masts, etc. the use of de-icing or adhesion-preventing liquids will provide the best means of protection."
Date:
August 1939
Creator:
Rothrick, A. M. & Selden, R. F.
System:
The UNT Digital Library
The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction
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.
System:
The UNT Digital Library
Aerodynamic Characteristics of Several Airfoils of Low Aspect Ratio
"This paper presents the results of wind-tunnel tests of several airfoils of low aspect ratio. The airfoils included three circular Clark Y airfoils with different amounts of dihedral, two Clark Y airfoils with slots in their portions, and three flat-plate airfoils. Lift, drag, and pitching-moment characteristics of the slotted airfoils with slots open and closed; pitching moment characteristics of one of the slotted airfoils with slots open and closed; and lift characteristics of the flat-plate airfoils are included" (p. 1).
Date:
August 1935
Creator:
Zimmerman, C. H.
System:
The UNT Digital Library
Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)
Report presenting an investigation in the low-turbulence pressure tunnel to determine the aerodynamic characteristics of NACA 64-010 and 0010-1.10 airfoil sections. The investigation covered a range of Mach and Reynolds numbers.
Date:
August 1954
Creator:
Loftin, Laurence K., Jr.
System:
The UNT Digital Library
Aerodynamic Characteristics of Three Deep-Step Planing-Tail Flying-Boat Hulls and a Transverse-Step Hull with Extended Afterbody
From Summary: "An investigation was made to determine the aerodynamic characteristics in the presence of a wing of three-step planning-tail flying-boat hulls which differed only in the amount of step fairing. The purpose of comparison, tests were also made of a transverse-step hull with an extended afterbody."
Date:
August 1952
Creator:
Riebe, John M. & Naeseth, Rodger L.
System:
The UNT Digital Library
Aerodynamic mixing downstream from line source of heat in high-intensity sound field
From Summary: "This report describes a theoretical and experimental investigation of the aerodynamic mixing by a standing sound wave downstream from a continuous line source of heat."
Date:
August 1956
Creator:
Mickelsen, William R. & Baldwin, Lionel V.
System:
The UNT Digital Library
The aerodynamics of a wind-tunnel fan
From Introduction: "This paper deals only with the aerodynamics of the fan proper and demonstrates the manner in which the radial distribution of axial velocity of fluid through a fan is governed by geometry of the fan itself."
Date:
August 1941
Creator:
Corson, Blake W.
System:
The UNT Digital Library
Air Flow Investigation for Location of Angle of Attack Head on a JN4h Airplane
The technical staff of the NACA at Langley Field, has made a series of free flight tests with a JN4h airplane in order to find the best place for an instrument for measuring the angle of attack. A "neutral zone" was found where the air remains either at rest relative to the undisturbed air beyond the influence of the airplane, or is set in motion parallel to the motion of the airplane. This zone is about midway between the two wings and slightly in front of, or at the vertical plane through the leading edges of the wings but the exact position as well as the outlines of the zone varies considerably as the conditions of flight change.
Date:
August 1925
Creator:
Freeman, R. G.
System:
The UNT Digital Library
Airfoil section characteristics at high angles of attack
From Introduction: "The present paper is concerned with certain aspects of the behavior of airfoil sections at high angles of attack with particular emphasis on the needs of the helicopter designer."
Date:
August 1954
Creator:
Loftin, Laurence K., Jr.
System:
The UNT Digital Library
Analysis of Cylinder-Pressure-Indicator Diagrams Showing Effects of Mixture Strength and Spark Timing
"An investigation was made to determine the effect of mixture strength and of normal as well as optimum spark timing on the combustion, on the cylinder temperature, and on the performance characteristics of an engine. A single-cylinder test unit utilizing an air-cooled cylinder and a carburetor and operating with gasoline having an octane rating of 92 was used. The investigation covered a range of fuel-air ratios from 0.053 to 0.118. Indicator diagrams and engine-performance data were taken for each change in engine conditions" (p. 1).
Date:
August 1940
Creator:
Gerrish, Harold C. & Voss, Fred
System:
The UNT Digital Library
Analysis of flow in a subsonic mixed-flow impeller
From Introduction: "A brief description of the method of analysis is presented herein considering the mean stream surface approach advanced in references 2 and 3, and both the incompressible and compressible solutions are given in detail."
Date:
August 1952
Creator:
Wu, Chung-Hua; Brown, Curtis A. & Costilow, Eleanor L.
System:
The UNT Digital Library
Analysis of laminar incompressible flow on semiporous channels
From Introduction: "Experimental results for flow in a rectangular channel with injection through a porous wall are given in reference 1. As part of the study to guide future experiments, laminar flow in a semiporous channel is investigated herein. In the present investigation, a third-order perturbation solution for laminar incompressible flow in a semiporous channel is presented."
Date:
August 1956
Creator:
Donoughe, Patrick L.
System:
The UNT Digital Library
Analysis of Landing-Gear Behavior
Note presenting an analytical study of the behavior of the conventional type of oleo-pneumatic landing gear during the process of landing impact. The basic analysis is presented in a general form and treats the motions of the landing gear prior to and subsequent to the beginning of shock-strut deflection.
Date:
August 1952
Creator:
Milwitzky, Benjamin & Cook, Francis E.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
Analysis of planing data for use in predicting hydrodynamic impact loads
From Introduction: "The magnitude of hydrodynamic loads experienced by seaplanes during a landing impact has been investigated experimentally and theoretically by the National Advisory Committee for Aeronautics. The results as reported in references 1 and 2 provide a rational means of determining loads on conventional V-bottom hulls in a step landing."
Date:
August 1948
Creator:
Steiner, Margaret F.
System:
The UNT Digital Library
An analysis of shock-wave cancellation and reflection for porous walls which obey an exponential mass-flow pressure-difference relation
From Introduction: "In the present report a generalized exponential relation between pressure difference and normal flow is assumed which adequately describes porous-wall calibrations obtained experimentally at the Ames Laboratory and those presented in references 1 and 3."
Date:
August 1954
Creator:
Spiegel, Joseph M. & Tunnell, Phillips J.
System:
The UNT Digital Library
An analysis of the normal accelerations and airspeeds of a four-engine airplane type in postwar commercial transport operations on trans-Pacific and Caribbean-South American routes
Report presenting an analysis of normal-acceleration and airspeed data on several transport airplanes of a four-engine type during postwar commerical operations on trans-Pacific and Caribbean-South American routes of the same airlines. The results indicate that the acceleration increment corresponding to the limit-gust-load-factor increment may be exceed about twice in all of the flight miles for each route. Results regarding accelerations, flight loads, gust encounters, and speeds are provided.
Date:
August 1950
Creator:
Coleman, Thomas L. & Schumacher, Paul W. J.
System:
The UNT Digital Library
An analysis of the power-off landing maneuver in terms of the capabilities of the pilot and the aerodynamic characteristics of the airplane
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.
System:
The UNT Digital Library
An analysis of the stability and ultimate bending strength of multiweb beams with formed-channel webs
From Introduction: "The purpose of the present paper is to develop a simple method of calculating both the stress at which initial wrinkling occurs in muti-web beams and the ultimate bending strength of beams which are susceptible to this mode of instability."
Date:
August 1954
Creator:
Semonian, Joseph W. & Anderson, Roger A.
System:
The UNT Digital Library
Analytical and Experimental Investigation of Aerodynamic Forces and Moments on Low-Aspect-Ratio Wings Undergoing Flapping Oscillations
"Aerodynamic forces and moments associated with flapping oscillations of finite wings at low speeds are considered. A comparison of theoretical and experimental results is made for a rectangular wing of aspect ratio 2. Calculated results are also given for three tapered wings of aspect ratio 3 with varying amounts of sweepback" (p. 1).
Date:
August 1958
Creator:
Woolston, Donald S.; Clevenson, Sherman A. & Leadbetter, Sumner A.
System:
The UNT Digital Library