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Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System

Description: Report presenting an analysis of the effects of heat and compressibility in the flow through the internal systems of aircraft. Equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date: September 1942
Creator: Becker, John V. & Baals, Donald D.
Partner: UNT Libraries Government Documents Department
open access

Comparison of tightness of 78 degrees machine-countersunk rivets driven in holes prepared with 78 degrees and 82 degrees countersinking tools

Description: Report presenting an investigation to determine whether the use of a 78 degree countersinking tool instead of a 82 degree countersinking tool for riveting would substantially alter the conclusion reached in a previous paper regarding the placement of rivets for maximum strength.
Date: September 1942
Creator: Gottlieb, Robert & Mandel, Merven W.
Partner: UNT Libraries Government Documents Department
open access

Condensation trails: Where they occur and what can be done about them

Description: Report presenting a brief, nontechnical discussion of condensation trails for flying personnel. World maps showing trail-forming zones at different altitudes and seasons are presented. Means for suppression trails are given.
Date: September 1942
Creator: Rhode, Richard V. & Pearson, H. A.
Partner: UNT Libraries Government Documents Department
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The critical compression load for a universal testing machine when the specimen is loaded through knife edges

Description: "The results of a theoretical and experimental investigation to determine the critical compression load for a universal testing machine are presented for specimens loaded through knife edges. The critical load for the testing machine is the load at which one of the loading heads becomes laterally instable in relation to the other. For very short specimens the critical load was found to be less than the rated capacity given by the manufacturer for the machine. A load-length diagram is proposed f… more
Date: September 1942
Creator: Lundquist, Eugene E. & Schwartz, Edward B.
Partner: UNT Libraries Government Documents Department
open access

A Description of the Ju 88 Airplane Anti-Icing Equipment

Description: Bulletin presenting an examination of a part of the anti-icing equipment for a Ju 88 airplane, including exhaust-air heat exchangers, control valves, air duct system, and air-heated wing panels. Testing was performed on the components and indicated that the thermal ice-prevention equipment can maintain the outer-wing panel free from ice.
Date: September 1942
Creator: Rodert, Lewis A. & Jackson, Richard
Partner: UNT Libraries Government Documents Department
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The Direct-Stress Fatigue Strength of 17S-T Aluminum Alloy Throughout the Range From 1/2 to 500,000,000 Cycles of Stress

Description: "Fatigue-tests were conducted on six specimens made from 3/4-inch-diameter 17S-T rolled-and-drawn rod for the purpose of obtaining additional data on the fatigue life of the material at stresses up to the static strength. The specimens were tested in direct tension using a stress range from zero to a maximum in tension. A static testing machine was used to apply repeated loads in the case of the first three specimens; the other three specimens were tested in a direct tension-compression fatigue… more
Date: September 1942
Creator: Hartmann, E. C. & Stickley, G. W.
Partner: UNT Libraries Government Documents Department
open access

Effect of Aromatics and Spark Advance on Thermal Efficiency

Description: Report presenting an analysis of experimental and theoretical data, which indicates that critical evaluation of fuel performance, especially economy, must be made in the engine. Data show that heating value is, from the aspect of fuel economy, not so important an aviation-fuel specification as believed. The knock ratings of fuels are affected by spark advance.
Date: September 1942
Creator: Gilbert, Mitchell
Partner: UNT Libraries Government Documents Department
open access

The Effect of Cowling Shape on the Stability Characteristics of an Airplane

Description: "Three widely different nose shapes were tested on a fuselage alone and on a complete model in the UACA stability tunnel to investigate the effect of cowling shape on stability characteristics. The results are presented in the form of charts which show the variation in the aerodynamic characteristics with the three nose shapes for the propeller-removed condition over a wide range of angles of attack and yaw. The results of the investigation indicated that large changes in the cowling shape prod… more
Date: September 1942
Creator: Donlan, C. J. & Letko, W.
Partner: UNT Libraries Government Documents Department
open access

Effect of Ground on Characteristics of Model of a Low-Wing Airplane With Full-Span Slotted Flap With and Without Power

Description: Report presenting ground-effect tests made in the LMAL 7- by 10-foot tunnel of a model of a low-wing, pursuit-type airplane equipped with a full-span 25-percent-chord slotted flap. Testing occurred at different heights and power conditions, and two stabilizer and elevator settings were used at each condition. Results indicated that the elevator deflection required for landing in a three-point attitude with the full-span slotted flap was considerably greater than that required with a partial-spa… more
Date: September 1942
Creator: Recant, I. G. & Wallace, A. R.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Valve Cooling Upon Maximum Permissible Engine Output as Limited by Knock

Description: "A Wright GR-1820-G200 cylinder was tested over a wide range of fuel-air ratios at maximum permissible power output as limited by knock with three different degrees of valve cooling. The valves used were stock valves (solid inlet valve and hollow sodium-cooled exhaust valve), hollow valves with no coolant, and hollow valves with flowing water as a coolant. Curves showing the variation in maximum permissible values of inlet-air pressure, indicated mean effective pressure, cylinder charge, and in… more
Date: September 1942
Creator: Munger, Maurice; Wilsted, H. D. & Mulcahy, B. A.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Aileron Characteristics of a Grumman F4F-3 Airplane

Description: "The aileron characteristics of a Grumman F4F-3 airplane were determined in flight by means of NACA recording and indicating instruments. The results show that the ailerons met NACA minimum requirements for satisfactory control throughout a limited speed range. A helix angle of approximately 0.07 radian was produced with flaps down at speeds from 90 to 115 miles per hour indicated airspeed and with flaps up from 115 to 200 miles per hour" (p. 1).
Date: September 1942
Creator: Kleckner, Harold F.
Partner: UNT Libraries Government Documents Department
open access

The Icing of Aircraft

Description: This technical memorandum presents a theoretical study of the processes accompanying the formation of ice on solid bodies. It discusses vapor pressure and sublimation in two air masses separated by a boundary area.
Date: September 1942
Creator: Robitzsch, M.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Hydrofoils in the NACA Tank 1: Effect of Dihedral and Depth of Submersion

Description: Tests were conducted on hydrofoil assemblies approximating an arrangement for use under seaplanes or surface boats. A series of hydrofoils, each supported by two struts, was towed at various depths ranging from partial submersions to a depth of 5-chord lengths. At depths greater than 4 or 5 chords, the influence of the surface of the water is small; hydrofoils operating at low speed will have characteristics similar to those of airfoils of the same section.
Date: September 1942
Creator: Benson, James M. & Land, Norman S.
Partner: UNT Libraries Government Documents Department
open access

An investigation of the effectiveness of stiffeners on shear-resistant plate-girder webs

Description: From Summary: "The results of 60 different tests on 2 aluminum alloy 17S-T plate girders are presented to show the influence of size and spacing of stiffeners upon the buckling characteristics of shear-resistant webs within the elastic range. It is demonstrated that stiffeners increase the stability of a web by retarding the formation subdivided panels. An empirical method of proportioning stiffeners is proposed which recognizes both of these stiffener functions, and comparisons are made with d… more
Date: September 1942
Creator: Moore, R. L.
Partner: UNT Libraries Government Documents Department
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Measurements of the Flying Qualities of a Supermarine Spitfire VA Airplane

Description: Report presenting the flying qualities of the Supermarine Spitfire airplane. A variety of information regarding the construction, installation, longitudinal stability and control, and lateral stability and control are provided.
Date: September 1942
Creator: Phillips, William H. & Vensel, Joseph R.
Partner: UNT Libraries Government Documents Department
open access

The Navier-Stokes Stress Principle for Viscous Fluids

Description: "The Navier-Stokes stress principle is checked in the light of Maxwell's mechanism of friction and in connection herewith the possibility of another theorem is indicated. The Navier-Stokes stress principle is in general predicated upon the conception of the plastic body. Hence the process is a purely phenomenological one, which Newton himself followed with his special theorem for one-dimensional flows" (p. 1).
Date: September 1942
Creator: Mohr, Ernst
Partner: UNT Libraries Government Documents Department
open access

Results of landing tests of various airplanes

Description: Report presenting a study of the landing characteristics of various airplanes with special attention paid to problems with landing gear design. The planes ranged from 1000 to 50,000 pounds and in span from 28 to 149 feet. Results regarding the observed landing conditions, including attitude, vertical velocity, pitching velocity, rolling velocity, lateral velocity (or side drift), and landing gear loads measured during the tests are provided.
Date: September 1942
Creator: Hootman, J. A. & Jones, A. R.
Partner: UNT Libraries Government Documents Department
open access

Some Lift and Drag Measurements of a Representative Bomber Nacelle on a Low-Drag Wing 2

Description: "Tests of a second representative bomber nacelle on a low-drag wing at a large value of the Reynolds number were made in the NACA two-dimensional low-turbulence pressure tunnel. Results show the drag and interference of the nacelle on the low-drag wing to be small" (p. 1).
Date: September 1942
Creator: Ellis, Macon C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Stalling Characteristics of the Supermarine Spitfire VA Airplane

Description: Report presenting an investigation of the stalling characteristics of the Supermarine Spitfire, which was made as part of the flying-qualities measurement of the airplane. The results are presented in the form of time histories of the motions and controls during stalls in various conditions of flight. Generally, the Spitfire possessed good stall warning in the form of buffeting and stall motions were not violent.
Date: September 1942
Creator: Vensel, J. R. & Phillips, W. H.
Partner: UNT Libraries Government Documents Department
open access

Tests of a Stress-Carrying Door in Compression

Description: Bulletin presenting the results of bending tests on a monocoque box with the door on the compression side. The results indicate that the effectiveness of a stress-carrying door depends on the intended function of the door.
Date: September 1942
Creator: Gottlieb, Robert
Partner: UNT Libraries Government Documents Department
open access

Tests of an NACA 66,2-420 Airfoil of 5-Foot Chord at High Speed, Special Report

Description: "This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds including the critical compressibility speed. Section coefficients of lift, drag, and pitching moment, and extensive pressure-distribution data are presented. The section drag coefficient at the design lift coefficient of 0.4 increased from 0.0042 at low speeds to 0.0052 at a Mach number of 0.56 (390 mph at 25,000 ft altitude). The critical Mach number was about 0.60. The results cover a Reynold num… more
Date: September 1942
Creator: Hood, Manley J. & Anderson, Joseph L.
Partner: UNT Libraries Government Documents Department
open access

Thermal Theory of Combustion and Explosion 3: Theory of Normal Flame Propagation

Description: The technical memorandum covers experimental data on flame propagation, the velocity of flame propagation, analysis of the old theoretical views of flame propagation, confirmation of the theory for simple reactions (theory of combustion of explosive substances and in particular nitroglycol), and check of the theory by example of a chain oxidizing reaction (theory of flame propagation in carbon monoxide, air and carbon monoxide - oxygen mixtures).
Date: September 1942
Creator: Semenov, N. N.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Development of Ailerons for the Curtiss XP-60 Airplane, Special Report

Description: An investigation was made in the LWAL 7- by 10-foot tunnel of internally balanced, sealed ailerons for the Curtiss XP-60 airplane. Ailerons with tabs and. with various amounts of balance were tested. Stick forces were estimated for several aileron arrangements including an arrangement recommended for the airplane. Flight tests of the recommended arrangement are discussed briefly in an appendix, The results of the wind-tunnel and flight tests indicate that the ailerons of large or fast airplanes… more
Date: September 1942
Creator: Rogallo, F. M. & Lowry, John G.
Partner: UNT Libraries Government Documents Department
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