Serial/Series Title
NACA Research Memorandums
4,120
NACA Technical Notes
2,223
Atomic Energy Commission Reports
1,874
United States Geological Survey Reports
1,253
Trace elements investigations report
749
Hanford Works Reports
710
University of California Radiation Laboratory Reports
484
HW (Series)
475
Oak Ridge National Laboratory Reports
440
NACA Technical Reports
382
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12,489 Matching Results
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Theoretical calculations of the supersonic pressure distribution and wave drag for a limited family of tapered sweptback wings with symmetrical parabolic-arc sections at zero lift
Report presenting the study of the supersonic pressure distribution and wave drag of sweptback wings at zero lift, which has been extended by means of linearized theory to include the combined effects of plan-form taper and curvature of profile. Calculations have been made for a specific wing with a supersonic leading edge, which are applicable to a limited family of plan forms.
Date:
January 1950
Creator:
Kainer, Julian H.
Object Type:
Report
System:
The UNT Digital Library
A Theoretical Investigation of the Effect on the Lateral Oscillations of an Airplane of an Automatic Control Sensitive to Yawing Accelerations
Report presenting an investigation to determine the effect on the lateral oscillations of an airplane of an automatic control sensitive to yawing accelerations. Results indicated that a control of that type can successfully damp the lateral oscillations through a reasonable range of time lag.
Date:
January 1950
Creator:
Beckhardt, Arnold R.
Object Type:
Report
System:
The UNT Digital Library
Tin Deposits of Durango, Mexico
From abstract: This report summarizes the economic possibilities of the tin deposits of the Estado de Durango, Mexico. It describes in detail many deposits in the leading districts, which were examined in 1944, and briefly reviews some reports on undeveloped occurrences in the southern and western parts of the State. The general conclusion is that tin will continue to be produced by hand methods for many years, but probably at a decreasing rate, because the placer grounds which have always produced the greater part of the tin are faced with gradual exhaustion.
Date:
1950
Creator:
Smith, Ward C.
Object Type:
Report
System:
The UNT Digital Library
Topical report on anion-exchange studies on the separation and purification of uranium and thorium
A report which describes the separation of uranium from thorium in carbonate, hydrochloric acid, and sulfuric acid solutions by anion-exchange resins.
Date:
1950
Creator:
Poirier, R. H. & Bearse, A. E.
Object Type:
Report
System:
The UNT Digital Library
Topical report on examination of residues from the nitric acid digestion of pitchblende
A report about an investigation started to determine the compounds and/or minerals present in the residue resulting from nitric acid digestion of ore. Emphasis was placed on determining the compounds and/or minerals containing boron.
Date:
1950
Creator:
Langston, B.; Tangel, O. F. & Richardson, A. C.
Object Type:
Report
System:
The UNT Digital Library
Transonic Stability and Control Investigation of a 1/80-Scale Model of the Consolidated Vultee Skate 9 Seaplane, TED No. NACA DE 345: Transonic-Bump Method
"An investigation of the longitudinal stability and of the all-movable horizontal tail and aileron control of a 1/80-scale reflection-plane model of the Consolidated Vultee Skate 9 seaplane has been made through a Mach number range of 0.6 to 1.16 on the transonic bump of the Langley high-speed 7- by 10-foot tunnel. At moderate lift coefficients (0.4 to 0.8) and below a Mach number of 1.0 the model was statically unstable longitudinally. The static longitudinal stability of the model at low lift coefficients increased with Mach number corresponding to a shift in aerodynamic center from 37 percent mean aerodynamic chord at a Mach number of 0.60 to 64 percent at a Mach number of 1.10" (p. 1).
Date:
1950
Creator:
Riebe, John M. & MacLeod, Richard G.
Object Type:
Report
System:
The UNT Digital Library
United States Earthquakes, 1950
Report discussing earthquake activity in the United States during 1950. The report is broken down by regions and has sections for specific earthquakes.
Date:
1950
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
The Use of Ether Extraction for the Analytical Separation of Uranium
This report follows experiments on ether extraction of uranium as a means of separation from other elements.
Date:
1950
Creator:
Furman, N. Howell; Mundy, R. J. & Morrison, George H.
Object Type:
Report
System:
The UNT Digital Library
Volcanic Activity in the Aleutian Arc
Including a list of all known volcanoes and a summary of activity betwen 1760 and 1948.
Date:
1950
Creator:
Coats, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Volcanoes of the Parícutin Region, Mexico
The following report describes the different volcanoes of the Paricutin Region.
Date:
1950
Creator:
Williams, Howel
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of a Full-Scale Model of the Hughes MX-904 Missile
"A wind-tunnel investigation has been conducted to determine the stability and control characteristics of a full-size model of the Hughes MX-904 missile. Aerodynamic characteristics of the complete model through moderate ranges of angles of attack and yaw, with an additional test made through an angle of attack of 180 degrees, are presented. The effects of horizontal tail deflection are also included" (p. 1).
Date:
1950?
Creator:
Wiley, Harleth G.
Object Type:
Report
System:
The UNT Digital Library
Tests of the Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Wing Modifications
"Wind-tunnel tests were conducted to determine the longitudinal stability characteristics of a full-scale Northrop XSSM-A-3 missile. Various wing modifications were investigated in an effort to provide a configuration that would maintain longitudinal stability to lift coefficients necessary for landing the missile during flight tests. The results of the tests led to the choice of a wing with an increased leading-edge radius" (p. 1).
Date:
January 5, 1950
Creator:
Graham, David
Object Type:
Report
System:
The UNT Digital Library
Effect of aspect ratio on the air forces and moments of harmonically oscillating thin rectangular wings in supersonic potential flow
This report treats the effect of aspect ratio on the air forces and moments of an oscillating flat rectangular wing in supersonic potential flow. The linearized velocity potential for the wing undergoing sinusoidal torsional oscillations simultaneously with sinusoidal vertical translations is derived in the form of a power series in terms of a frequency parameter. The series development is such that the differential equation for the velocity potential is satisfied to the required power of the frequency parameter considered and the linear boundary conditions are satisfied exactly. The method of solution can be utilized for other plan forms, that is, plan forms for which certain steady-state solutions are known.
Date:
January 6, 1950
Creator:
Watkins, Charles E.
Object Type:
Report
System:
The UNT Digital Library
Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Bevelled-Trailing-Edge Flap and Trim Tab by the NACA Wing-Flow Method
The third investigation in a series to determine the fundamental characteristics of trailing-edge controls at transonic speeds. This particular report uses a 35 degree sweptback untapered airfoil model with an aspect ratio of 3 and a flap with a bevelled trailing edge with a trailing-edge angle of 23 degrees. Results regarding lift, pitching-moment, and hinge-moment characteristics are provided.
Date:
January 6, 1950
Creator:
Johnson, Harold I. & Brown, B. Porter
Object Type:
Report
System:
The UNT Digital Library
Aeronautical study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at supersonic speeds of a model with the wing twisted and cambered for uniform load
Report presenting the lift, drag, and pitching-moment characteristics of a wing-fuselage combination employing a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at a lift coefficient of 0.25 and Mach number 1.53. The experimental results are compared to those from other investigations. A maximum lift-drag ratio of 8.9 and a minimum drag coefficient of 0.0145 was obtained.
Date:
January 9, 1950
Creator:
Hall, Charles F. & Heitmeyer, John C.
Object Type:
Report
System:
The UNT Digital Library
Preparation of Ductile Zirconium: Progress Report for December 1949
Report discussing progress made by the National Research Corporation in developing preparation of ductile zirconium for the month of December, 1949.
Date:
January 10, 1950
Creator:
DiPietro, W. O.; Findlay, G. R. & Stauffer, R. A.
Object Type:
Report
System:
The UNT Digital Library
Production of Pi-Mesons in Lead by High Energy Proton Bombardment
Our knowledge of the properties of mesons and their interactions with nuclei has come from two sources. Studies of cosmic ray phenomena provided the earliest information. The discovery that mesons may be produced artificially by bombardment of nuclei with radiations from high energy accelerators has, on the other hand, made it feasible to undertake a wide variety of investigations under more controlled conditions than is possible in cosmic ray experiments. In such experiments mesons have been produced by high-energy protons, alpha-particles and neutrons.
Date:
January 10, 1950
Creator:
Weissbluth, Mitchel
Object Type:
Report
System:
The UNT Digital Library
Exploratory Investigation of the Effect of Skewed Plain Nose Flaps on the Low-Speed Characteristics of a Large-Scale Triangular-Wing-Fuselage Model
Memorandum presenting an investigation of the effect of skewed plain nose flaps on a thin, low-aspect-ratio triangular wing in combination with a high fineness-ratio fuselage conducted at low speeds and high Reynolds numbers. The plan form of the flaps was such that the flap chord varied from zero percent of the wing chord at the model center line to 100 percent at about 91-percent wing semispan. The results indicated that the nose flaps provided a significant delay in the occurrence of both the leading-edge type of separation and tip stalling.
Date:
January 12, 1950
Creator:
Wick, Bradford H. & Graham, David
Object Type:
Report
System:
The UNT Digital Library
Results Obtained During Flights 1 to 6 of the Northrop X-4 Airplane (A.F. No. 46-677)
Report presenting testing using a Northrop X-4 to obtain stability and control data during airplane acceptance tests. The data includes a time history of a complete pull-up, time histories of several level and accelerated flight runs, and the effect of dive-brake extension on the longitudinal and lateral trim.
Date:
January 12, 1950
Creator:
Matthews, James T., Jr.
Object Type:
Report
System:
The UNT Digital Library
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.
Date:
January 12, 1950
Creator:
Mitchell, Jesse L. & Peck, Robert F.
Object Type:
Report
System:
The UNT Digital Library
A Lift-Cancellation Technique in Linearized Supersonic-Wing Theory
"A lift-cancellation technique is presented for determining load distributions on thin wings at supersonic speeds. The loading on a wing having a prescribed plan form is expressed as the loading of a known related wing (such as a two-dimensional or triangular wing) minus the loading of an appropriate cancellation wing. The lift-cancellation technique can be used to find the loading on a large variety of wings. Applications to swept wings having curvilinear plan forms and to wings having reentrant side edges are indicated" (p. 65).
Date:
January 16, 1950
Creator:
Mirels, Harold
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Investigation of the Aerodynamic Loads on the Droop-Nose Flap of a Wing With Leading Edge Swept Back 47.5 Degrees and Having Symmetrical Circular-Arc Airfoil Sections at a Reynolds Number of 4.3 X 10 (Exp 6)
Report presenting an investigation of the pressure distribution on the full-span droop-nose flap of a wing with the leading edge swept back 47.5 degrees and symmetrical circular-arc airfoil sections. Flap pressure distributions were obtained for the base configuration and various deflections of the full-span droop-nose flap and other flap deflection combinations. Information regarding the flow and section characteristics, spanwise loading parameters, center-of-pressure variation, and flap normal-force and hinge-moment coefficients is provided.
Date:
January 16, 1950
Creator:
Whittle, Edward F., Jr. & Fink, Marvin P.
Object Type:
Report
System:
The UNT Digital Library
Measurements of the Drag and Pressure Distribution on a Body of Revolution Throughout Transition From Subsonic to Supersonic Speeds
Memorandum presenting an investigation of the drag and pressure distribution on a body of revolution of fineness ratio 12 as measured by the free-fall method. Analysis of the results has provided knowledge of the mechanism of the abrupt drag rise which occurs near the speed of sound, and demonstrates that the theoretical method described in a previous report satisfactorily predicts the shape of the measured pressure distributions at low supersonic speeds.
Date:
January 16, 1950
Creator:
Thompson, Jim Rogers
Object Type:
Report
System:
The UNT Digital Library
The effect of tip tanks on the rolling characteristics at high subsonic Mach numbers of a wing having an aspect ratio of 3 with quarter-chord line swept back 35 degrees
Report presenting an investigation of the effect of wing-tip mounted tanks on the rolling characteristics of a wing, aspect ratio 3 with the quarter-chord line swept back 35 degrees, through a range of Mach numbers and angles of attack using the free-roll method.
Date:
January 17, 1950
Creator:
Kuhn, Richard E. & Myers, Boyd C., II
Object Type:
Report
System:
The UNT Digital Library