Technical Report Archive & Image Library (TRAIL) - 533 Matching Results

Search Results

prev Results: 169 - 192 next
open access

Experimental Studies of the Knock-Limited Blending Characteristics of Aviation Fuels 1: Preliminary Tests in an Air-Cooled Cylinder

Description: Report presenting an investigation of the relation between the knock limit and the blend composition of aviation fuels when tested under supercharged conditions in an air-cooled aircraft-engine cylinder. Results regarding the blending characteristics of two gasolines, paraffinic fuels, olefinic fuel, naphthenic fuel, aromatic fuels, when xylidines are present in the fuel components, and fuel components containing unequal concentrations of tetraethyl lead are provided.
Date: October 1944
Creator: Sanders, Newell D.; Hensley, Reece V. & Breitwieser, Roland
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental survey of flow across banks of elliptical and pointed tubes

Description: Report presenting an experimental survey of the details of the flow of fluids across banks of streamline tubes as a continuation of previous work. Information that clarifies the picture of flow has been obtained by surveys of total, dynamic, and static pressure, and hot-wire cooling surveys of the unheated tubes.
Date: January 1943
Creator: Joyner, Upshur T. & Palmer, Carl B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Verification of the Rudder-Free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction

Description: "An investigation has been made in the Langley free-flight tunnel to obtain an experimental verification of the theoretical rudder-free stability characteristics of an airplane model equipped with conventional rudders having negative floating tendencies and negligible friction. The model used in the tests was equipped with a conventional single vertical tail having rudder area 40 percent of the vertical tail area. The model was tested both in free flight and mounted on a strut that allowed free… more
Date: November 1944
Creator: McKinney, Marion O. & Maggin, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Extended Tables of Stiffness and Carry-Over Factor for Structural Members Under Axial Load

Description: Report presenting an extension of tables of stiffness and carry-over factor to include the stiffness of a member with the far end subjected to a moment equal and opposite to the moment applied at the near end. The formulas used in calculation to determine the values are also provided.
Date: February 1944
Creator: Lundquist, Eugene E. & Kroll, W. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fatigue Characteristics of Spot-Welded 24S-T Aluminum Alloy

Description: Report presenting the results of an investigation of the fatigue characteristics of spot-welded 24S-T aluminum alloy. The static shear strength of spot welds in lap joints of 24S-T alclad increases with increasing sheet thickness for thicknesses in the range of 0.025 inch to 0.032 inch.
Date: June 1943
Creator: Russell, H. W.; Jackson, L. R.; Grover, H. J. & Beaver, W. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fatigue Strength and Related Characteristics of Aircraft Joints 1: Comparison of Spot-Weld and Rivet Patterns in 24S-T Alclad and 75S-T Alclad

Description: Report contains detailed results of a number of fatigue tests on spot-welded joints in aluminum alloys. The tests described include: (1) fatigue tests on spot-welded lap joints in sheets of unequal thickness of alclad 24s-t. These tests indicate that the fatigue strength of a spot-welded joint in sheets of two different gages is slightly higher than that of a similar joint in two sheets of the thinner gage but definitely lower than that of a similar joint in two sheets of the thicker gage. (2) … more
Date: December 1944
Creator: Russell, H. W.; Jackson, L. R.; Grover, H. J. & Beaver, W. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fatigue strength and related characteristics of joints in 24S-T Alclad sheet

Description: Report includes tension fatigue test results on the following types of samples of 0.040-inch alclad 24s-t: (1) monoblock sheet samples as received and after a post-aging heat treatment, (2) "sheet efficiency" samples (two equally stressed sheets joined by a single transverse row of spot welds) both as received and after post-aging, (3) spot-welded lap-joint samples as received and after post-aging, and (4) roll-welded lap-joint samples. (author).
Date: May 1944
Creator: Russell, H. W.; Jackson, L. R.; Grover, H. J. & Beaver, W. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fatigue Strength and Related Characteristics of Spot-Welded Joints in 24S-T Alclad Sheet

Description: Report presenting an investigation on spot-welded 24S-T Alclad. The report is divided into five parts, including an investigation of tension fatigue measurements, lap-joint samples spot-welded by different companies, fatigue strengths of wire-stitched lap-joint samples, data on similar samples with different spot spacings, and the results of compression fatigue tests for stiffened panels with purposely overheated spot welds.
Date: December 1943
Creator: Russell, H. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fatigue Strength of Flush-Riveted Joints for Aircraft Manufactured by Various Riveting Methods

Description: Report presenting the results of an investigation to determine the fatigue strength of flush-riveted joints manufactured by different riveting methods. Tests were made on a direct stress fatigue machine at room temperature. The results showed that the fatigue strength of the joints was directly affected by the method of riveting used.
Date: December 1945
Creator: Maney, G. A. & Wyly, L. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Fatigue Tests of Riveted Joints : Progress Report of Tests of 17S-T and 53S-T Joints

Description: Report presenting the fatigue data obtained at the Aluminum Research Laboratories from tests of various types of 17S-T and 53S-T specimens. The specimens were large enough to represent actual service conditions, but the repetition of loading was more rapid than would occur in ordinary service.
Date: September 1944
Creator: Hartmann, E. C.; Lyst, J. O. & Andrews, H. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flame-visibility tests with individual exhaust stacks

Description: Report presenting testing made on a Wright 1820-G single-cylinder engine to determine the effect of operating variables and the effect of shape and size of the exhaust stack on the visibility of exhaust gases for individual-stack installations. Flame damping was improved by decrease in nozzle-exit area, increase in stack length, and reduction in hydraulic diameter of the exhaust jets. Results regarding the characteristics of exhaust flames and damping of exhaust flames are provided.
Date: February 1944
Creator: Turner, L. Richard & Humble, Leroy V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of an NACA ice-detector suitable for use as a rate-of-icing indicator

Description: Report presenting an ice detector that can serve as a basis for a rate-of-icing indicator. The instrument consists of a wire screen and a pitot tube mounted behind the screen with both enclosed in a cylindrical shell. Observed data and some possibilities for future development are provided.
Date: November 1942
Creator: Gilruth, R. R.; Zalovcik, J. A. & Jones, A. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Boundary-Layer and Profile-Drag Characteristics of Smooth Wing Sections of a P-47D Airplane

Description: "In Mach range of 0.25 - 0.69, boundary-layer measurements were made on upper wing surface at 25% semi-span, pressure-distribution measurements made on upper surface at 63% semi-span, and wake surveys made at 63% semi-span. The minimum profile-drag coefficient of 0.0062 was indicated for smooth section at 63% semi-span. Critical mach number was exceeded by 0.04, but no compressibility shocks appeared. In slipstream, boundary layer transition occurred as far back as 20% chord on upper surface at… more
Date: October 1945
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight investigation of fuselage static-pressure-vent airspeed installations

Description: Report presenting an investigation to determine the departure of the static pressure measured at fuselage static-pressure vents from the static pressure of the ambient air. Several locations for fuselage static-pressure vents on an XB-24F and a Lockheed 12A airplane.
Date: November 1943
Creator: Scherrer, Richard & Rodert, Lewis A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of Internally Balanced Sealed Ailerons

Description: "Flight tests were made of a type of internally balanced sealed ailerons installed on a Ryan ST airplane. Aileron effectiveness and stick forces were measured at various airspeeds under NACA recording instruments. For comparison, the aileron characteristics were also determined without the internal balance and seals" (p. 1).
Date: December 1941
Creator: Williams, W. C. & Kleckner, H. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap

Description: Report presenting flight tests made with a modified Ryan ST airplane to determine the effect on aileron characteristics of various arrangements of balanced split flaps covering that portion of the wing span occupied by the ailerons. With the flaps fully extended, the aileron effectiveness was reduced by approximately 18 percent of the effectiveness measured with ailerons alone.
Date: May 1942
Creator: Williams, W. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of NACA D(Sub S) Cowlings on the XP-42 Airplane 1: High-Inlet-Velocity Cowling with Propeller Cuffs Tested in High-Speed Level Flight

Description: Report presenting results from a series of flight tests of the maximum speed and cooling characteristics in full-throttle level flight of the XP-42 airplane equipped with a short-nose high-inlet velocity cowling. The results of the tests indicated a maximum speed of 336 miles per hour at 960 horsepower at 25,000 feet. Results regarding maximum speed and pressure and temperatures are provided.
Date: January 1943
Creator: Bailey, F. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 2: low-inlet-velocity cowling with axial-flow fan and propeller cuffs

Description: Report presenting results from a series of flight tests of the performance and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a short-nose low-inlet-velocity cowling and an axial-flow fan mounted on the spinner. Results regarding maximum speed and pressures and temperatures are provided.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 3: low-inlet-velocity cowling without fan or propeller cuffs, with axial-flow fan alone, and with two different sets of propeller cuffs

Description: Report presenting the results of flight measurements of performance and cooling characteristics of the XP-42 airplane equipped with a short-nose low-inlet-velocity cowling. Testing included measurements in level flight and climb of the effects of a spinner-mounted axial-flow fan without propeller cuffs, no fan or cuffs, and two different sets of propeller cuffs.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of NACA D(sub S) cowlings on the XP-42 airplane 4: high-inlet-velocity cowling tested in climb with and without propeller cuffs and in high-speed level flight without propeller cuffs

Description: Report presenting flight measurements of the performance and cooling characteristics of a short-nose high-inlet-velocity cowling on the XP-42 for conditions of climb with and without propeller cuffs and for high speed without cuffs. The speed of the airplane was approximately 1 mile per hour greater without propeller cuffs than the previously measured value with cuffs. Results regarding maximum speed, pressures and temperatures, and ground cooling are provided.
Date: January 1943
Creator: Johnston, J. Ford & Voglewede, T. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight investigation of short-period longitudinal oscillations of an airplane with free elevator

Description: Report presenting a flight investigation to check the results of a theoretical analysis of longitudinal stability of an airplane with free controls. Tests used a Fairchild XR2K-1 airplane on which the weight moment and the aerodynamic balance of the elevator were varied to bring it into a condition where unstable short-period oscillations were encountered.
Date: May 1942
Creator: Phillips, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of the Effect of Surface Roughness on Wing Profile Drag With Transition Fixed

Description: Report presenting a flight investigation made on a wing section of a P-47D airplane to determine the effect of roughness on wing profile drag with transition fixed far forward. Surveys of the wake were made for two surface conditions with transition fixed by a thread at 5 percent chord back of the leading edge on the upper and lower surfaces. Below the Mach number at which shock occurred, variations in Mach number of as much as 0.16 appeared to have no appreciable effect on the section profile-… more
Date: September 1944
Creator: Zalovcik, John A. & Wood, Clotaire
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight investigation of the performance and cooling characteristics of a long-nose high-inlet-velocity cowling on the XP-42 airplane

Description: Report presenting the results of a series of flight tests of the maximum speed and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a long-nose high-inlet-velocity cowling. The results indicated that a maximum speed of 338 miles per hour at 870 horsepower at 17,000 feet was achievable, which is above the engine critical altitude. Pressure measurements in the entrances in the cylinder baffles showed a uniform distribution of pressure on the fron… more
Date: April 1942
Creator: Bailey, F. J., Jr.; Johnston, J. Ford & Voglewede, T. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of the Thermal Properties of an Exhaust Heated Wing De-Icing System on a Lockheed 12-A Airplane

Description: "The thermal properties are presented for the exhaust heated wing de-icing system of a Lockheed 12-A airplane which has successfully prevented a wing icing in 25 hours of flying in various icing conditions. The quantities of heat supplied for de-icing of the wings under various conditions were measured and are presented. The distribution of temperatures above the ambient air temperature for the wing surface under various operating conditions are given" (p. 1).
Date: June 1941
Creator: Rodert, Lewis A. & Clousing, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen