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Restraint Provided a Flat Rectangular Plate by a Sturdy Stiffener Along an Edge of the Plate, Special Report
A sturdy stiffener is defined as a stiffener of such proportions that it does not suffer cross-sectional distortion when moments are applied to some part of the cross section. When such a stiffener is attached to one edge of a plate, it will resist rotation of that edge of the plate by means of its torsional properties. A formula is given for the restraint coefficient provided the plate by such a stiffener. This coefficient is required for the calculation of the critical compressive stress of the plate.
A restricted list of aircraft materials research projects
This report contains a selected list of Government sponsored research projects on related aircraft materials in effect during the calendar year 1947. Information is contained on titles, description, sponsoring and conducting agencies.
Results obtained during accelerated transonic tests of the Bell XS-1 airplane in flights to a Mach number of 0.92
Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87. Buffeting has been experienced in level flight but it has been mild and the associated tail loads have been small. No aileron buzz or other flutter phenomena have been noted.
Results obtained during extension of U.S. Air Force transonic-flight tests of XS-1 airplane
No Description Available.
Results obtained during flights 1 to 6 of the Northrop X-4 airplane (A.F. no. 46-677)
No Description Available.
Results obtained from second flight of X-4 airplane (A.F. no. 46-676)
No Description Available.
Results Obtained from Third Flight of Northrop X-4 Airplane (A.F. No. 46-676)
NACA instrumentation has been installed in the Northrop X-4 airplane to obtain stability and control data during the Northrop conducted acceptance tests. The results o. the third flight of the X- ll. number 1 airplane are presented in this paper. The results of this flight showed that the directional stability as measured in steadily increasing sideslips was positive and high and that the lateral stability was positive.
Results of a Biological Reconnaissance of the Yukon River Region
Brief summary of the Yukon River region, including itinerary of expedition, faunal districts, new species identified, and mammals and birds present.
Results of a Biological Reconnoissance of South-Central Idaho
Brief summary of south-central Idaho, including descriptions of subregions, mammals, birds, and reptiles.
Results of a Biological Survey of Mount Shasta California
From introduction: "Biological survey of northern California from the Madeline Plains to the Pacific Ocean and from the Oregon boundary to Lassen Butte and parts of the Sierra, with Mount Shasta occupying a nearly central position."
Results of a Biological Survey of the San Francisco Mountain Region and Desert of the Little Colorado, Arizona
Brief summary of a biological survey of the Painted Desert, specifically the San Francisco Mountain region, and the Grand Canyon (Cañon).
Results of a flight investigation to determine the zero-lift drag characteristics of a 60 degree delta wing with NACA 65-006 airfoil section and various double-wedge sections at Mach numbers from 0.7 to 1.6
No Description Available.
Results of a Force Test of Four Configurations of the Hi-Lo Instrumented and Chaff Rockets in the Sandia Corporation 12 x 12 inch Transonic Wind Tunnel (Program III-46)
Abstract: Force, moment, and center of pressure information are presented for four models of the Hi-Lo configuration.
Results of a power-on flight of a 1/10-scale rocket-propelled model of the convair xf2y-1 airplane at a mach number of 1.53
No Description Available.
Results of a rocket-model investigation of control-surface buzz and flutter on a 4-percent-thick unswept wing and on 6-, 9-, and 12-percent-thick swept wings at transonic speeds
No Description Available.
Results of aerodynamic tests on slotted airfoils in the aerotechnical laboratory (S.T. Ae.) of Rhode St. Genese, Brussels
We have investigated the maximum lift obtainable with slotted airfoils derived from a symmetrical airfoil. These should have a smaller profile drag than other slotted airfoils.
Results of Air-Water and Steam-Water Tests on Radial Vane Steam Separator Models
From introduction: "Describes progress in the development of radial vane primary separators following initial work reported in GEAP 3564."
Results of an Airborne Radiometric Survey in the Canon City Embayment Area, Colorado
Abstract: An airborne radiometric survey of the Dakota sandstone and Morrison formation in the Canon City embayment was conducted by the Atomic Energy Commission from November 1, 1953 to December 5, 1953.
Results of an experimental investigation of small viscous dampers
No Description Available.
Results of an investigation at high subsonic speeds to determine lateral-control and hinge-moment characteristics of a spoiler-slot-deflector configuration on a 35 degree sweptback wing
No Description Available.
Results of Assays of the New Albany Oil-Shale
Report issued by the U.S. Bureau of Mines on a survey of the New Albany oil-shale deposits in Indiana. The experimental procedures for surveying and sampling these shale deposits are presented in detail. This report includes tables, and graphs.
Results of ATR Sample Fuel Plate Irradiation Experiment
From abstract: "Fuel materials proposed for use in the Advanced Test Reactor were evaluated."
Results of axial-load fatigue tests on electropolished 2024-T3 and 7075-T6 aluminum-alloy-sheet specimens with central holes
No Description Available.
Results of edge-compression on stiffened flat-sheet panels of alclad and nonclad 14S-T6, 24S-T3, and 75S-T6 aluminum alloys
No Description Available.
Results of Electrical Resistivity and Electrical Induction Measurements at Abana Mine, Quebec, Canada: Explanation of Some Factors Associated with Induction Method
Technical paper issued by the Bureau of Mines over studies conducted on electrical resistivity at the Abana Mine in Quebec. The methods used, and results of the studies are discussed. This paper includes tables, maps, and illustrations.
Results of experimental flights at high altitudes with Daimler, Benz and Maybach engines to determine mixture formation and heat utilization of fuel
The experimental flights described herein were made with the object of obtaining information regarding the following two questions, which as yet have not been sufficiently elucidated. These are: 1. What effect has altitude upon the formation of the mixture? 2. What alteration takes place, with increasing altitude, in the utilization of the heat contained in the fuel?.
Results of experiments with slotted wings
This report recounts some of the successful experiments conducted in England and Germany on slotted wings and ailerons. Wind tunnel test results are given and examples of aircraft constructed with these new wing components are described.
Results of extended tests of the Focke-Wulf F 19a "ente," a tail-first airplane
These investigations consisted chiefly of measurements of the take-off distance under various starting conditions and with the c.g. in different positions; of the climbing speed as a function of the impact pressure and location of the c.g.; of the longitudinal stability and fore-and-aft controllability and of the determination of the elevator forces and characteristics of the elevator control.
Results of Flight Test of an Automatically Stabilized Model C (Swept Back) Four-Wing Tiamat
The results of the first flight test of a swept-back four-wing version of Tiamat (MX-570 model C) which was launched at the NACA Pilotless Aircraft Research Station at W4110PB Island, Va. are presented. In general, the flight behavior was close to that predicted by calculations based an stability theory and oscillating table tests of the autopilot. The flight test thus indicates that the techniques employed to predict automatic stability are valid and practical from an operational viewpoint. The limitations of the method used to predict flight behavior arise from the fact that the calculations assume no coupling among roll, pitch, and yaw, while in actual flight some such coupling does exist.
Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag
No Description Available.
Results of flight tests to determine drag of parabolic and cone-cylinder bodies of very large fineness ratios at supersonic speeds
Results of a free-flight investigation at supersonic speeds to determine zero-lift drag of a series of bodies of revolution are presented. Configurations tested included two parabolic bodies with fineness ratios of 17.78 and 24.5 and two 8 degree cone-cylinder bodies with fineness ratios of 17.2 and 21.2. Results of previous tests of similar parabolic bodies but with lower fineness ratios are included in this paper for comparison. All bodies for which data are presented in this paper had a base-to-maximum-diameter ratio of 0.437. Calculated drag coefficients are shown for all bodies for which data are presented. (author).
Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3
No Description Available.
Results of free-flight test of 1/10-scale model of the Convair XF2Y-1 airplane between Mach numbers of 0.7 and 1.45, including power-on flight at Mach number 1.2 : TED No. NACA DE 365
No Description Available.
Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores
No Description Available.
Results of landing tests of various airplanes
No Description Available.
Results of measurements made during the approach and landing of seven high-speed research airplanes
No Description Available.
Results of measurements of maximum lift and buffeting intensities obtained during flight investigation of the Northrop X-4 research airplane
The variation of the intensity of buffeting experienced throughout the operational region of the semitailless Northrop X-4 airplane and the values of maximum and peak normal-force coefficients in the Mach number range from 0.42 to 0.92 have been determined. The results are compared with data obtained with the swept-wing Douglas D-558-II airplane.
Results of preliminary flight investigation of aerodynamic characteristics of the NACA two-stage supersonic research model RM-1 stabilized in roll at transonic and supersonic velocities
No Description Available.
Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25
Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Results of Primary Triangulation and Primary Traverse: Fiscal Year 1902-03
From introduction: This report contains the results of the primary triangulation and primary traverse executed by the USGS during the fiscal year 1902-3.
Results of Primary Triangulation and Primary Traverse: fiscal year 1903-04
From introduction: This report contains the results of primary triangulation and primary traverse in the eastern and western divisions of the United States.
Results of recent experiments with slotted wings
This report gives the results of a recent series of experiments performed on a wing designed for a cantilever monoplane. Both wings were trapezial in their ground plan, with their tips rounded elliptically. These wing sections combine all known devices for increasing the lift, namely, the slot, the increased camber and angle of attack by means of an aileron running the whole length of the span. The last advance included in the wing section was an increase in wing area by means of an auxiliary wing adjusted by a sort of rectangular joint.
Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage : lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3
No Description Available.
Results of shear fatigue tests of joints with 3/16-inch-diameter 24S-T31 rivets in 0.064-inch-thick alclad sheet
No Description Available.
Results of tests on radiators for aircraft engines
Part 1 is to present the results of tests on 56 types of core in a form convenient for use in the study of the performance of and possible improvements in existing designs. Working rules are given by which the data contained in the report may be used, and the most obvious conclusions as to the behavior of cores are summarized. Part 2 presents the results of tests made to determine the pressure necessary to produce water flows up to 50 gallons per minute through an 8-inch square section of radiator core. These data are of special value in evaluating the hydraulic head against which the circulating pump is required to operate.
Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds
Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coeeficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90
No Description Available.
Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90 : TED No. NACA AD 3115
No Description Available.
Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models
The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.
Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range
Results of four thin, unswept, flutter airfoils attached to two freely falling bodies are reported. Two airfoils fluttered at a Mach number of 0.85, a third airfoil fluttered at a Mach number of 1.03, and a fourth fluttered at a Mach number of 1.07. Results of calculations of flutter speed using incompressible and compressible air-force coefficients, including a Mach number of 1.0, are presented.