UNT Libraries Government Documents Department - 310 Matching Results

Search Results

Results: 1 - 24 next
open access

Accelerations Measured at Center of Gravity and Along Span of the Wing of a B-24D Airplane in Landing Impacts

Description: Report presenting measurements of a Consolidated B-24D airplane of accelerations at various points on the wing during landing impacts. landings were made with the wheels initially stationary but free to rotate, with the brakes set before contact, and with the main wheels rotating prior to contact.
Date: August 1944
Creator: Westfall, John R.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils From Tests in the NACA Two-Dimensional Low-Turbulence Pressure Tunnel

Description: Report presenting two low-drag airfoils, the NACA 747A315 and the NACA 747A415, which are designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient and are tested in the tow-dimensional low-turbulence pressure tunnel.
Date: September 1944
Creator: von Doenhoff, Albert E. & Stivers, Louis S., Jr.
Item Type: Refine your search to only Report
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
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
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
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
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
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
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
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
open access

Analysis of Vertical-Tail Loads in Rolling Pull-Out Maneuvers

Description: Bulletin presenting an analysis of the vertical-tail loads to be expected as a result of abrupt aileron action in accelerated flight, as in rolls from turns or pull-outs, for example. Critical tail loads may occur in rolling pull-out maneuvers, particularly on airplanes with good ailerons and low directional stability.
Date: August 1944
Creator: Gilruth, Robert R.
Item Type: Refine your search to only Report
open access

An Analytical Investigation of the Effects of Elevator-Fabric Distortion on the Longitudinal Stability and Control of an Airplane

Description: From Summary: "The results of an analytical investigation to determine the qualitative effects of elevator-fabric distortion on the stick-force characteristics of an airplane are presented. These results indicate that serious alteration of intended stick-force characteristics can be produced by elevator-fabric distortion."
Date: May 1944
Creator: Mathews, Charles W.
Item Type: Refine your search to only Report
open access

Application of Spring Tabs to Elevator Controls

Description: Report presenting equations for calculating the stick-force characteristics obtained with a spring-tab type of elevator control. The main problems encountered in the design of the satisfactory elevator spring tab are to provide stick forces in the desired range, to maintain the force per g sufficiently constant throughout the speed range, to avoid undesirable "feel" of the control in ground handling, and to prevent flutter.
Date: October 1944
Creator: Phillips, William H.
Item Type: Refine your search to only Report
open access

Artificial Running-in of Piston Rings

Description: Report presenting a consideration of the performance of sliding surfaces, such as piston rings, cylinders, journals, and bearings in aircraft engines with reference to the surface characteristics that they possess before and after running-in, prior to service operation. The phenomena accompanying the running-in process are analyzed.
Date: March 1944
Creator: Bobrowsky, A. R. & Machlin, E. S.
Item Type: Refine your search to only Report
open access

An Automatically Variable Control Linkage and Its Effect on the Lateral-Control Characteristics of a High-Speed Fighter Airplane

Description: Report discusses an analysis and preliminary design of a control linkage that varies automatically with dynamic pressure. The advantages of the device, including greater lateral control than a fixed control linkage without additional aerodynamic balance, are detailed. The effect of variable linkage on lateral-control characteristics is also described.
Date: May 1944
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
open access

Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam With a Mass at Its Tip

Description: Report discusses an investigation into the behavior of a cantilever beam in transverse motion with a mass at its tip when the root is suddenly brought to rest. Equations for determining the stresses, deflections, and accelerations that arise in the beam are also provided. This testing can be applied to the shock created in an airplane when landing and the vibrations that result.
Date: November 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B.; Houbolt, John C. & Schmieder, Albert K.
Item Type: Refine your search to only Report
open access

Breaking Aircraft-Engine Oil Foams by Use of Electrically Charged Condenser Plates

Description: Report presenting a determination of the effectiveness of a charged condenser for breaking oil foams and to obtain data on which to base the design of such a device for mounting at the oil-tank inlet of an airplane. Results regarding the condenser-plate area and arrangement, wet-plate design, condenser voltage, oil temperature, water in oil, and some safety considerations are provided.
Date: November 1944
Creator: Pinkel, I. Irving
Item Type: Refine your search to only Report
Back to Top of Screen