Technical Report Archive and Image Library (TRAIL) - 1,263 Matching Results

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Acceleration, stress, and deflection measurements on the XB-15 bomber in gusty air
From Introduction: "This report presents the results of these tests which cover a total of about 70 flying hours on this airplane."
Accelerations and bottom pressures measured on a B-24D airplane in a ditching test
From Introduction: "This report presents only that portion of the data from the first ditching which was to be used roughly establish the accelerations experienced by the pilot and the amount of water pressure to which the fuselage structure was subjected during the ditching."
Accelerations measured at center of gravity and along span of the wing of a B-24D airplane in landing impacts
No Description Available.
Addition of heat to a compressible fluid in motion
From Introduction: "The purpose of this report is to summarize, without extended proofs, the results of a study of a simplified model of nonadiabiatic, compressible fluid flow, both subsonic and supersonic, and to state these results in a form that will make them immediately useful in providing a theoretical background for current technical problems of high-speed combustion.
Additional design charts relating to the stalling of tapered wings
From Introduction: "The present report, therefore, may be considered a supplement to reference 1. The combined scope of the stall charts of reference 1, designated A, and of the present work, designated B, is summarized in the following table: For the wing with root thickness ratio to 18 was also investigated.
An additional investigation of the high-speed lateral-control characteristics of spoilers
No Description Available.
Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps
No Description Available.
Adjustment of stick force by a nonlinear aileron-stick linkage
No Description Available.
The advantages of uniform fuel distribution for air-cooled engines from considerations of cooling requirements and fuel economy
No Description Available.
Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body: NACA model 84 series
Report presenting a series of related flying-boat hull forms with various combinations of aerodynamic and hydrodynamic requirements that were tested in an NACA tank and high-speed tunnel. Effects explored included varying the height of the bow, varying the height of the stern, increasing the angle of dead rise at the bow, decreasing the angle of dead rise on the afterbody, increasing the depth of step, increasing the angle of afterbody keel, adding chine flare, adding a third planing surface, and rounded chines at the bow.
Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil
From Introduction: "The results of the load tests and some additional aerodynamic characteristics of perforated double split flaps on a rectangular NACA 23012 airfoil are given in the present report."
Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel
From Introduction: "The data are presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap comoinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and lower (slotted) flap."
Aerodynamic characteristics for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane
Report presenting testing in the two-dimensional turbulence tunnel of a model of the tip section of the wing of the XP-63 airplane. Several alterations of the skirts and balance on the internal-balance aileron were tested to obtain various aerodynamic characteristics of the aileron.
Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage
No Description Available.
Aerodynamic characteristics of a 4-engine monoplane showing comparison of air-cooled and liquid-cooled engine installations
From Introduction: "An investigation has been conducted in the N.A.C.A. full-scale wind tunnel to determine the aerodynamic characteristics of a 1/4-scale model of a 4-engine monoplane when equipped with comparable air-cooled engine and liquid-cooled engine installations. The air-cooled engine installation consisted of nacelles equipped with N..A.C.A. cowlings and oil coolers located in the leading edge of the wing."
Aerodynamic characteristics of a 4-engine monoplane showing effects of enclosing the engines in the wing and comparisons of tractor- and pusher-propeller arrangements
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.
Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes
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."
Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotor blades
From Introduction: "The purpose of the present work is to extend the previous investigation and to derive additional airfoil sections designed to minimize the undesirable characteristics of the previously tested airfoils. The tests of these additional airfoils were made in the Langley two-dimensional low-turbulence tunnel (LTT)."
Aerodynamic characteristics of several modifications of a 0.45-scale model of the vertical tail of the Curtiss XP-62 airplane
From Introduction: "In the course of an investigation to find a satisfactory vertical tail for the XP-62 airplane, a 0.45-scale vertical tail model on a stub fuselage was tested in the Langley 7- by 10-foot tunnel. This model was fitted with a flat plate to represent the horizontal tail surface. The data are presented herein for their general interest value rather than their application to this particular airplane."
Aerodynamic characteristics of the NACA 747A315 and 747A415 airfoils from tests in the NACA two-dimensional low-turbulence pressure tunnel
No Description Available.
Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap
No Description Available.
Aerodynamic factors affecting the ability of a pilot to return an airplane to level from a banked attitude by use of the rudder alone and without change of heading
No Description Available.
Aerodynamic problems in the design of efficient propellers
From General Analysis: "The purpose of part I of this paper is to show how the loading that gives the minimum induced energy loss can be obtained from rather elementary considerations and to present design charts from which such a plan form can be quickly obtained for any set of design conditions."
Aerodynamic tests of a full-scale TBF-1 aileron installation in the Langley 16-foot high-speed tunnel
From Summary: "This report describes tests in the Langley 16-foot high-speed tunnel to determine whether these failures could be attributed to changes in the aerodynamic characteristics of the ailerons at high speeds."
Aerodynamic tests of an AN-M-65-AEON 1000-pound radio-controlled bomb in the LMAL 16-foot high-speed tunnel
No Description Available.
Aerodynamic tests of an M-31 bomb in the 8-foot high-speed tunnel
No Description Available.
Aerodynamic tests of an NACA 66(215)-116, a=0.6 airfoil with a 0.25c slotted flap for the Fleetwings XA-39 airplane
No Description Available.
The aerodynamic tests of three Edo floats for the SB2U-3, 0S2U-2, and XSB2C-2 seaplanes - NACA models 106-K, 107-K, and 125-AH
Report presenting aerodynamic testing of scale models of the Edo seaplane floats for the SB2U-3, OS2U-2, and XSB2C-2 seaplanes. Various coefficients, pitching moment, yawing moment, and drag coefficients are provided.
Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane
From Introduction: "An investigation of the power-plant installation of a single-engine torpedo-bomber-type airplane has been conducted in the NACA Cleveland altitude wind tunnel at the request of the Bureau of Aeronautics, Navy Department. A similar investigation was previously conducted on a three-tenths scale mock-up of the forward portion of the fuselage of this airplane in the Langley 20-foot tunnel. (See reference 1)."
Air-consumption parameters for automatic mixture control of aircraft engines
From Introduction: "The purpose of this analysis was to investigate the use of function of intake-manifold temperature and pressure, exhaust back pressure, and engine speed in place of a ventri as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Air-flow and performance characteristics of engine-stage supercharger of a double-row radial aircraft engine II : effect of design variables
No Description Available.
Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables
From Introduction: "The tests reported herein, conducted during the early part of 1945, were made to determine the inherent charge-air distribution characteristics of the engine-stage supercharger of the double-row radial engine."
Air-flow surveys in the region of the tail surfaces of a single-engine airplane equipped with dual-rotating propellers
From Summary: "Surveys of the air flow in the region of the tail surfaces of a single-engine pursuit-type airplane equipped with dual-rotating propellers are presented."
Airfoil-contour modifications based on (epsilon)-curve method of calculating pressure distribution
From Introduction: "Certain alternations of a qualitative nature may be performed in spite of the fact that a pressure change cannot be prescribed. It is the purpose of this paper to indicate a method by which qualitative alternation may be performed. It will be noted that the present method of contour modification will serve the intended purpose of the inverse method."
Airfoil section data from tests of 10 practical- construction sections of helicopter rotor blades submitted by the Sikorsky Aircraft Division, United Aircraft Corporation
No Description Available.
Airspeed fluctuations as a measure of atmospheric turbulence
From Introduction: "Increments in structural loads due to atmospheric turbulence can be accurately expressed in terms of flight speed and effective gust velocities (reference 4). Data from which the effective gust velocities could be computed were also obtained during the flights of the XC-35 airplane. These data have been used to determine the significance of the fluctuations in the pilot's indicated-airspeed readings in relation to structural loads to due to atmospheric turbulence."
Altitude rating of electrical apparatus
From Introduction: "This paper studies the effect of altitude on the ratings of rotating electric machines and after determining the fundamental principles involved, discusses these in relation to the application of such machines in modern aircraft."
Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter
From Introduction: "The research program included clean-up tests (unpublished data) and stability and control tests (reference 1) made in the NACA Langley full-scale tunnel. An investigation of the aerodynamic characteristics of the power-plant installation in the Cleveland altitude wind tunnel is discussed in this report."
Aluminum-zinc-magnesium-copper casting alloys
From Introduction: "This paper contains data on the mechanical properties of sand-cast test bars having a considerable range in zinc, magnesium, and copper content and more detailed data on the properties and foundry characteristics of an aluminum-zinc-magnesium-copper alloy having a preferred composition for high strength and ductility."
Analysis and correlation of data obtained by six laboratories on fuel-vapor loss from fuel tanks during simulated flight
No Description Available.
Analysis of a thermal ice-prevention system for wing leading-edge landing-light installations
From Introduction: "A typical ice formation on a wing leading-edge-type light installation is shown in figure 1. Although the primary purpose of this analytic investigation was to determine the practicability of providing a landing-light thermal ice-prevention system which could be incorporated with the wing leading-edge thermal ice-prevention system of the B-17 F airplane, the analysis has been developed in a general form for future application to similar deigns. "
Analysis of available data on control surfaces having plain-overhang and Frise balances
From Introduction: "The present paper deals with control surfaces having plain-overhang and Frise balances."
Analysis of available data on the effectiveness of ailerons without exposed overhang balance
From Introduction: "As a part of the general lateral-control investigation by the NACA, the large amount of two- and three-dimensional data on the rolling effectiveness of ailerons without exposed overhang balance is collected and analyzed in the present paper."
Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter Airplane
An analysis was made to determine the effect of rolling pull-out maneuvers on the wing and aileron loads of a typical fighter airplane, the P-47B. The results obtained indicate that higher loads are imposed upon wings and ailerons because of the rolling pull-out maneuver, than would be obtained by application of the loading requirements to which the airplane was designed. An increase of 102 lb or 15 percent of wing weight would be required if the wing were designed for rolling pull-out maneuver. It was also determined that the requirements by which the aileron was originally designed were inadequate.
Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes
From Introduction: "The lift increments of different flap arrangements were determined by the method of reference 1 with a simple chord correction factor being applied. This procedure is somewhat similar in basic principles to the method of reference 2. The accuracy of the present method was determined by calculating by means of this method the lift and moment increments of flaps on 10 different finite wing-flap combinations for which wind-tunnel data were available."
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system
No Description Available.
An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle
From Summary: "The results of the analysis showed that the combined efficiency, which is unacceptably low at speeds less than 300 miles per hour, becomes nearly equal to that of conventional power plants of current design at 500 miles per hour. It was also shown that the efficiency will be increased considerably as the physical limitations on cycle temperature and blower speed are raised and as the efficiencies of the system components are improved."
An analysis of life expectancy of airplane wings in normal cruising flight
From Summary: "The independent variables considered in the analysis included stress-concentration factor, stress-load relation, wing loading, design and cruising speeds, design gust velocity, and airplane size. Several methods for estimating fatigue life from gust frequencies are discussed."
The analysis of strains indicated by multiple-strand resistance-type wire strain gages used as rosettes
From Summary: "Methods are given for making the necessary corrections to the strains indicated by multiple-strand resistance-type wire strain gages used singly or as rosettes to measure strains at an angle to the principal strain. The results of tests to determine the validity of the methods of correction are reported."
An analysis of the effect of core structure and performance on volume and shape of cross-flow tubular intercoolers
From Introduction: "The purpose of this paper is to show, in a similar manner, the effect of change in the core structure of the tubular intercooler on the over-all dimensions when the operating conditions are fixed."