Technical Report Archive & Image Library (TRAIL) - 107 Matching Results

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Aerodynamic Characteristics of a 4-Engine Monoplane Showing Effects of Enclosing the Engines in the Wing and Comparisons of Tractor- and Pusher-Propeller Arrangements

Description: Report presenting testing in the full-scale wind tunnel on a model of a large 4-engine monoplane to determine the overall aerodynamic efficiency of a conventional wing-nacelle-engine installation as compared with power-plant installations enclosed in the wing with extension shafts to the propellers. Results regarding power-on and power-off performance for the installations as well as propeller noise are provided.
Date: April 1938
Creator: Silverstein, Abe & Wilson, Herbert A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a Slot-Lip Aileron and Slotted Flap for Dive Brakes

Description: From Introduction: "As a part of this investigation, a study is being made of test results obtained during the development of devices designed primarily for other purposes, such as high lift or lateral control, but which may also be used for dive control. These results have been reanalyzed and are herein presented in a form that should make them convenient for design purposes."
Date: April 1941
Creator: Rogallo, F. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculation of tab characteristics for flight conditions from wind-tunnel data

Description: Report presenting tail-surface characteristics calculated from wind-tunnel data, which have been reported to not correspond with flight-test measurements. The primary problem under consideration is the calculation of the effect of tab deflection on the free-floating angle of the elevator, as in a servocontrol.
Date: April 1942
Creator: Sears, Richard I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of the BMW 801D2 Automatic Engine Control as Determined From Bench Tests

Description: Report discusses the results of bench testing on a German BMW 301D2 to determine the relation between the control parameters and any special methods by which the control principles are adapted to the control of the engine. Characteristics are presented for a variety of simulated manifold pressures, charge-air temperatures, engine speeds, and altitudes. Special attention is paid to the pressure characteristics of the servo-oil system and the potential effects of its failure on the operation of t… more
Date: April 1945
Creator: Scharer, M. E. & Addie, A. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparative Cooling of Cylinders of Nonuniform Fin Width With Tight-Fitting Baffles and With Baffles That Provide Constant Flow-Path Areas

Description: Report presenting an investigation using tight-fitting baffles on the cooling fins of several modern air-cooled engine cylinders in order to maintain a constant free-flow area from the front to the rear of each interfin air passage. Results regarding the effect of restriction in cooling-air flow paths on cylinder temperature and effect of restrictions in cooling-air flow paths on cooling-air mass flow are provided.
Date: April 1944
Creator: Schey, Oscar W.; Rollin, Vern G. & Buckner, Howard A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil with Various Types of Aileron

Description: Sectional characteristics of airfoil having retractable slotted flap with plain, slot-lip, or retractable ailerons are presented for a large range of aileron deflections. The analysis indicated that pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness, also that pitching moments created by the spoiler increased less with the Mach number than similar moments produced by plain flaps. Positive values of pitching moment decreased as devi… more
Date: April 1945
Creator: Purser, Paul E. & McKinney, Elizabeth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Predicted and Actual Control-Fixed Stability and Control Characteristics of a Douglas A-26B Airplane

Description: Report presents a comparison of predicted qualities of the A-26B airplane with actual flying qualities determined in testing. From Summary: "The results indicate that the control-fixed, power-off stability and control characteristics of a conventional airplane can be predicted from the dimensions of the airplane and from general wind-tunnel data now available with sufficient accuracy for design purposes. No estimate of control forces, of effects of power on stability, or of adverse aileron yaw … more
Date: April 1945
Creator: Crane, Harold L. & Sjoberg, Sigurd A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of the compressive strength of panels with Alclad 24S-T81 sheet or with Alclad 24S-T86 sheet riveted to Alclad 24S-T84 hat-section stiffeners

Description: From Summary: "Compression tests were made of two groups of panel specimens with hat-section stiffeners. The groups were identical except that the flat sheet of one group was Alclad 24S-T81 and of the other Alclad 24S-T86. Results of the tests are given in tables or charts which show the average stress at which the sheet buckles and the average stress at the maximum load."
Date: April 1944
Creator: Weinberger, Robert A.; Rossman, Carl A. & Fisher, Gordon P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Yaw Characteristics of a Single-Engine Airplane Model With Single-Rotating and Dual-Rotating Propellers

Description: Report presenting testing in the pressure tunnel to determine the yaw characteristics of a scale model of a single-engine, fighter-type airplane with six-blade single-rotating and dual-rotating propellers. Force and moment characteristics are presented for several model and power conditions.
Date: April 1944
Creator: Neely, R. H.; Fogarty, L. E. & Alexander, S. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Computation of Hinge-Moment Characteristics of Horizontal Tails from Section Data

Description: Bulletin presenting a study of data from various wind-tunnel tests of horizontal tail surfaces to determine the accuracy with which section data can be used to estimate the hinge-moment characteristics of control surfaces of finite span. The study consisted of a comparison between the variations of elevator hinge moments with elevator deflection and with airplane pitching moment, as estimated from data obtained in two-dimensional flow, and that variation measured experimentally on 16 different … more
Date: April 1945
Creator: Crane, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Construction of Finned Aluminum Muffs for Aircraft Engine Cylinder Barrels

Description: "This report describes the material, cutting-tool development, and machining procedure used in constructing an air-cooled cylinder barrel having a cooling muff with 2-inch fins spaced 1/8 inch. Details of two types of thread form used for the barrel to head assembly with the cooling muff are also presented" (p. 1).
Date: April 1942
Creator: Langley Memorial Aeronautical Laboratory
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Cooling Correlation Equation for a Double-Row Radial Engine Based on the Temperature of the Exhaust-Valve Seat

Description: Report discussing a cooling-correlation equation based on the average temperature of exhaust-valve seats of a large double-row radial engine. From the equation, predicts can be made about the cooling-air pressure drop required to cool the critical region of engine cylinders. Using a modified carburetor to improve the fuel-air-ratio distribution to the cylinders increased the accuracy of the equation's predictions.
Date: April 1945
Creator: Jagger, James M. & Black, Fred O., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Correlation of Wind-Tunnel Predictions With Flight Tests of a Twin-Engine Airplane 1: Longitudinal-Stability and -Control Characteristics

Description: "The longitudinal-stability and -control characteristics of a twin-engine patrol airplane as predicted from the results of wind-tunnel tests of a powered model and as measured in flight are compared in this report. The accuracy of the wind-tunnel predictions and the reasons for discrepancies are analyzed and discussed" (p. 1).
Date: April 1945
Creator: Delany, Noel K. & Kauffman, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Description: Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high va… more
Date: April 1946
Creator: Pardee, Otway O'M. & Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The cross-flow plate-type intercooler

Description: Report presenting a mathematical analysis of plate-type intercooler design for both turbulent and laminar flow. Charts are presented to show how the plate-type intercooler volume, weight, plate area, frontal area, and linear dimensions can be varied without changing the intercooler operating conditions. An experimental investigation was also carried out with a plate-type intercooler unit to check the validity of the heat-transfer and pressure-drop theories for the airflow between very closely s… more
Date: April 1942
Creator: Pinkel, Benjamin; Reuter, J. George & Valerino, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design of Nozzles for the Individual Cylinder Exhaust Jet Propulsion System

Description: Report presenting an examination of the design of exhaust-stack nozzles for individual cylinder exhaust-gas jet propulsion and the results of tests on the effect of nozzle area on jet thrust and engine power. A satisfactory method of correlatig the test data for various engine-operating conditions is developed.
Date: April 1941
Creator: Pinkel, Benjamin; Turner, L. Richard & Voss, Fred
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ditching Tests With 1/16-Size Models of the Army B-17 Airplane in Langley Tank Number 2 and on an Outdoor Catapult

Description: Report presenting tests with dynamically similar models made to study the behavior of the Army B-17F and B-17G when ditched and to determine the best way to land them in calm and rough water. Various landing attitudes, speeds, and conditions of damage were simulated. The ideal landing condition was found to be in a three-point landing attitude and with the flaps 45 degrees at the slowest possible speed.
Date: April 1945
Creator: Tarshis, Robert P. & Stewart, Thelma
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ditching tests with a 1/16-size dynamic model of the Army B-24 airplane in Langley tank number 2 and on an outdoor catapult

Description: Testing conducted to determine the best way to ditch the Army B-24 airplane in calm and rough water and to determine its probable ditching performance. A dynamically similar model was ditched in calm water in tank no. 2 and calm and rough water from an outdoor catapult. Results regarding the effect of attitude and speed, effect of flap setting, effect of vertical velocity, effect of location of center of gravity, effect of simulated damage, effect of ditching aids, effect of fuselage length, ef… more
Date: April 1945
Creator: Fisher, Lloyd J. & Steiner, Margaret F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Coaxial Lapping of Cast-Iron Piston Rings on Ring Performance

Description: Report presenting a series of 25-hour accelerated high-output tests run on a single-cylinder aircraft-type spark-ignition engine to determine the effect of coaxial lapping of piston rings prior to engine operation. Standard cast-iron rings were used and tested with all rings lapped and with only the oil-control rings lapped. The results indicated that coaxial lapping with loose abrasive reduced both wear and scuffing.
Date: April 1944
Creator: Shames, Sidney J.; Machlin, Eugene S. & Wilson, John G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Fuel Volatility and Mixture Temperature on the Knocking Characteristics of a Liquid-Cooled Single-Cylinder Test Engine

Description: Report discussing an investigation to determine the effect of fuel volatility on the relation between mixture temperature and knock-limited performance on a liquid-cooled single-cylinder test engine. The mixture temperature at which the curve of indicated mean effective pressure plotted against mixture temperature becomes nonlinear was found to be independent of fuel volatility. The effects of vaporization on the knock-limited power output are also described.
Date: April 1945
Creator: Tauschek, Max J. & Lietzke, A. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of NACA Injection Impeller and Ducted Head Baffles on Flight Cooling Performance of Double-Row Radial Engine in Four-Engine Heavy Bomber

Description: "The NACA has conducted a flight investigation to improve the cooling characteristics of the installation of a double-row radial engine. The tests reported herein concern the use of the NACA injection impeller and ducted head baffles in various combinations on both the port inboard and the port outboard engines. The performance of the modified installation was evaluated by comparing it with that of the standard engines" (p. 1).
Date: April 13, 1945
Creator: Marble, Frank E.; Miller, Mahlon A. & Vensel, Joseph R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of spring and gravity moments in the control system on the longitudinal stability of the Brewster XSBA-1 airplane

Description: Report presenting calculations to determine the effects of spring and gravity moments in the control system on the longitudinal-stability characteristics of the Brewster XSBA-1 airplane, and the computed results have been verified by flight tests.
Date: April 1942
Creator: Phillips, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Valve Clearance on Knock-Limited Performance and Engine Cooling

Description: Report discussing the effect of valve clearance on valve-lift diagrams, knock-limited performance, and engine cooling. The performance of single-cylinder and multicylinder engines was also compared across these variables.
Date: April 1945
Creator: Cook, Harvey A.; Richard, Paul H. & Brown, Kenneth D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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