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

Search Results

prev Results: 25 - 48 next
open access

Aerodynamic Tests of an A-M-65-AZON 1000-Pound Radio-Controlled Bomb in the LMAL 16-Foot High-Speed Tunnel

Description: Report presenting tests made in the LMAL 16-foot high-speed tunnel to determine the aerodynamic characteristics of a 1000-pound AN-M-65-AZON radio-controlled bomb at a Mach number range of 0.2 to 0.6. Over the Mach number range, the hinge-moment coefficients, yawing-moment coefficients, and lateral-force coefficients exhibited no important changes with increasing speed.
Date: June 1944
Creator: Pearson, E. O., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Tests of an M-31 Bomb in the 8-Foot High-Speed Tunnel

Description: Report presenting aerodynamic tests of a 300-pound M-31 demolition bomb. Force tests at a range of angles of attack were made at Mach number 0.725, which corresponds to a speed of 810 feet per second at sea level. Results regard the drag, lift, and pitching moment are provided.
Date: August 1942
Creator: Baals, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Tests of an NACA 66(215)-116, a=0.6 Airfoil With a 0.25c Slotted Flap for the Fleetwings XA-39 Airplane

Description: Report presenting testing in the two-dimensional low-turbulence tunnels on a 24-inch-chord model of the NACA 66(215)-116 a = 0.6 airfoil with a 0.25-chord slotted flap. The optimum flap pivot positions were found for three different conditions. The conditions were determined from a consideration of the landing, take-off, and strafing requirements of the airplane.
Date: November 1944
Creator: Cahill, Jones F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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.
Date: March 1942
Creator: Liddell, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane

Description: 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)."
Date: June 1946
Creator: Palter, Herman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Air-consumption parameters for automatic mixture control of aircraft engines

Description: 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."
Date: September 1944
Creator: Shames, Sidney J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Air-Flow and Performance Characteristics of Engine-Stage Supercharger of a Double-Row Radial Aircraft Engine 2: Effect of Design Variables

Description: Report presenting an investigation to determine the effect of the location of the diffuser vanes with respect to the supercharger outlets and the effect of flow conditions at the impeller inlet on the air-flow distribution in the outlets of the engine-stage supercharger of an 18-cylinder double-row radial aircraft engine. The effect of flow conditions at the impeller inlet was investigated by distorting the flow at the inlet and noting the effect in the supercharger outlets. Results regarding t… more
Date: August 1946
Creator: Baas, Edmund J. & Dugan, Paul D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables

Description: 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."
Date: August 1945
Creator: Mesrobian, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Airfoil-Contour Modifications Based on (Epsilon)-Curve Method of Calculating Pressure Distribution

Description: 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."
Date: July 1944
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation

Description: Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.
Date: September 1944
Creator: Tetervin, Neal
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Airspeed Fluctuations as a Measure of Atmospheric Turbulence

Description: "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" (p. 3).
Date: July 1945
Creator: Tolefson, H. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Rating of Electrical Apparatus

Description: "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" (p. 1).
Date: January 1943
Creator: Lebenbaum, Paul, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter

Description: 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."
Date: February 1946
Creator: Preston, G. Merritt; Black, Fred O., Jr. & Jagger, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aluminum-Zinc-Magnesium-Copper Casting Alloys

Description: 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."
Date: July 1941
Creator: Kempf, L. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis and Correlation of Data Obtained by Six Laboratories on Fuel-Vapor Loss From Fuel Tanks During Simulated Flight

Description: Report presenting an analysis of data on fuel-vapor loss from fuel tanks during simulated flight obtained by six laboratories to show the effects of individual variables such as altitude, initial fuel temperature, rate of climb, booster-pump agitation, fuel depth, fuel-surface area, types of fuel, and vent-line pressure drop on fuel-vapor loss.
Date: December 1944
Creator: Stone, Charles S.; Baker, Sol & Englert, Gerald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of a thermal ice-prevention system for wing leading-edge landing-light installations

Description: 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. "
Date: January 1944
Creator: Hillendahl, Wesley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of available data on the effectiveness of ailerons without exposed overhang balance

Description: 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."
Date: May 1944
Creator: Crandall, Stewart M. & Swanson, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter Airplane

Description: 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… more
Date: March 1946
Creator: Pearson, Henry A. & Aiken, William S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes

Description: 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."
Date: September 1944
Creator: Maggin, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of Jet-Propulsion Systems Making Direct Use of the Working Substance of a Thermodynamic Cycle

Description: 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."
Date: February 1945
Creator: Rubert, Kennedy F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of life expectancy of airplane wings in normal cruising flight

Description: 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."
Date: July 1945
Creator: Putnam, Abbott A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen