Resource Type
Collection
Serial/Series Title
NACA Wartime Reports
26
NACA Advanced Restricted Reports
12
NACA Memorandum Reports
6
NACA Restricted Bulletins
4
NACA Advanced Confidential Reports
3
NACA Technical Notes
3
Atomic Energy Commission Reports
2
United States Bureau of Mines Reports
2
CC (Series) (Chicago, Illinois)
1
CP (Series) (Chicago, Illinois)
1
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Thermodynamic Design of Double-Panel, Air-Heated Windshields for Ice Prevention
Report details the development of design equations for double-panel, air-heated windshields with ice prevention properties. The application of the equations and suggestions for experimental flight testing are described.
Date:
June 1943
Creator:
Kushnick, Jerome L.
System:
The UNT Digital Library
Briquetting Subbituminous Coal
Report issued by the Bureau of Mines over briquetting of coal for development of more effective fuel. Materials, equipment, and processes are discussed. This report includes tables, illustrations, and photographs.
Date:
June 1943
Creator:
Parry, V. F. & Goodman, John B.
System:
The UNT Digital Library
Technical Division weekly progress report for period ending May 29, 1943
This report details Technical Division activities for the week ending May 29, 1943.
Date:
June 1, 1943
Creator:
unknown
System:
The UNT Digital Library
Technical Division weekly progress report for period ending June 5, 1943
This report details Technical Division activities for the week ending June 5, 1943.
Date:
June 8, 1943
Creator:
unknown
System:
The UNT Digital Library
Weekly progress report -- Technical Section for period ending June 12, 1943
Progress was reported from the 300, 100, and 200 Areas. It covered the X pile, aluminium corrosion, graphite purity, fuel element fabrication, bismuth phosphate extraction and decontamination processes, waste disposal from bismuth phosphate processing, control rod systems for Site W, shielding problems at the Site W separation plant, fuel element failure detection, power distribution in the Clinton pile, reactor instrumentation for Site W.
Date:
June 15, 1943
Creator:
unknown
System:
The UNT Digital Library
The Contamination of Cooling Water by a P-9 Plant
The following sources of contamination in cooling water of the P-9 plant are considered: (1) Fission recoils, (2) Corrosion of metal, (3) Recoil from aluminum, (4) Induced activity in the water. It is found that for a P-9 plant of 3.5 x 10(4) KW contamination of the river at "X" should not exceed the .1 r criterion unless coating failure occurs. Tables of the amount of coating failure permissible are given as a function of holdup time.
Date:
June 1, 1943
Creator:
Friedman, Francis L. (Francis Lee), 1918-
System:
The UNT Digital Library
PROGRESS REPORT ON METALLURGY OF TUBALLOY TO UNIVERSITY OF CHICAGO
None
Date:
June 10, 1943
Creator:
unknown
System:
The UNT Digital Library
Resume of Hinge-Moment Data for Unshielded Horn- Balanced Control Surfaces
Report summarizes the available hinge-moment data for unshielded horn-balanced control surfaces. The purpose is to correlate the available data to assist with estimating the balance characteristics for use in the design and alteration of control surfaces with horn balances. Plan forms and variation of incremental hinge-moment-coefficient slopes with balance coefficients are presented.
Date:
June 1943
Creator:
Lowry, John G.
System:
The UNT Digital Library
Wind-tunnel tests of ailerons at various speeds 2: ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil
Report presenting hinge-moment, lift, pressure difference across the balance, and pressure-distribution measurements in the two-dimensional test section of the stability tunnel on a 0.60 aileron-chord sealed internal-balance aileron on a specified NACA airfoil. The primary test objective was to determine the effect of speed on the action of the aileron.
Date:
June 1943
Creator:
Denaci, H. G. & Bird, J. D.
System:
The UNT Digital Library
Wind Tunnel Tests of Ailerons at Various Speeds 1: Ailerons of 0.20 Airfoil Chord and True Contour With 0.35 Aileron-Chord Extreme Blunt Nose Balance on the NACA 66,2-216 Airfoil
"Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed" (p. 1).
Date:
June 1943
Creator:
Letko, W.; Denaci, H. G. & Freed, C.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Control-Surface Characteristics 14: NACA 0009 Airfoil With a 20-Percent-Chord Double Plain Flap
Report discusses the results of force testing of the aerodynamic characteristics of an NACA 0009 airfoil with a double plain flap; it consisted of a plain forward flap with a chord 20 percent of the airfoil chord and a plan rearward flap with a chord 15 percent of the airfoil chord. Comparisons were made to the characteristics of a 0.50c single plain flap. The lift, hinge moments, drag, and pitching moments are described.
Date:
June 1943
Creator:
Sears, Richard I. & Purser, Paul E.
System:
The UNT Digital Library
Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane 1: Measurements of Flying Qualities With Original Tail Surfaces
Report presenting a series of tests of the Brewster XSBA-1 airplane conducted to determine the effect of various tail modifications. The current report describes an investigation of flying qualities of the airplanes with its original tail surfaces. Testing regarding longitudinal stability and control and stalling characteristics are provided.
Date:
June 1943
Creator:
Phillips, W. H. & Nissen, J. M.
System:
The UNT Digital Library
Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane
Report presenting flight tests of an all-movable vertical tail of reduced area of the Fairchild XR2K-1 airplane. Results are in agreement with previously obtained data on a larger all-movable tail. Results regarding rudder effectiveness, directional stability, rudder-free lateral motion, rudder hinge moments, and areas of future research are provided.
Date:
June 1943
Creator:
Kleckner, Harold F.
System:
The UNT Digital Library
Experimental Determination of the Yawing Moment Due to Yawing Contributed by the Wing, Fuselage, and Vertical Tail of a Midwing Airplane Model
Report presenting values of the lateral-stability derivative, the rate of change of yawing-moment coefficient with yawing angular velocity, contributed by the wing, the fuselage, and the vertical tail, which have been determined for a midwing airplane model by the free-oscillation method.
Date:
June 1943
Creator:
Campbell, John P. & Mathews, Ward O.
System:
The UNT Digital Library
Wind-tunnel vibration tests of a four-blade single rotating pusher propeller
Report presenting vibration tests of a four-blade single-rotating propeller operating in a simulated pusher condition performed because the combination of wake and downwash behind a wing might provide serious excitation for reactionless vibrations of propellers with four or more blades. Measurements of propeller vibratory stress were made for various airspeeds, engine speeds, and engine powers.
Date:
June 1943
Creator:
Miller, Mason F.
System:
The UNT Digital Library
Recommended Test Procedure for Aircraft Engine Turbosupercharger Power Plants
Report describes a procedure for instrumenting, testing, and presenting the overall characteristics of any engine turbosupercharger installation. The preflight analysis of the system, required testing, importance of accurate data recording, measurements to record, methods of measuring, and presentation of results are also included.
Date:
June 1943
Creator:
NACA Subcommittee on Recovery of Power from Exhaust Gas
System:
The UNT Digital Library
Adaptor for Measuring Principal Strains With Tuckerman Strain Gage
Report discussing an adapter which uses three Tuckerman optical strain gages to measure the displacement of the three vortices of an equilateral triangle along lines 120 degrees apart. These displacements are substituted in well-known equations in order to compute the magnitude and direction of the principal strains. Tests of the adaptor indicate that principal strains over a gage length of 1.42 inch may be measured with a systematic error not exceeding 4 percent and a mean observational error of the order of + or minus 0.000006. The maximum observed error in strain was of the order of 0.00006. The directions of principal strains for unidirectional stress were measured with the adaptor with an average error of the order of 1 degree.
Date:
June 1943
Creator:
McPherson, A. E.
System:
The UNT Digital Library
The Exact Solution of Shear-Lag Problems in Flat Panels and Box Beams Assumed Rigid in the Transverse Direction
"A mathematical procedure is herein developed for obtaining exact solutions of shear-lag problems in flat panels and box beams: the method is based on the assumption that the amount of stretching of the sheets in the direction perpendicular to the direction of essential normal stresses is negligible. Explicit solutions, including the treatment of cut-outs, are given for several cases and numerical results are presented in graphic and tabular form. The general theory is presented in a from which further solutions can be readily obtained" (p. 1).
Date:
June 1943
Creator:
Hildebrand, Francis B.
System:
The UNT Digital Library
Bearing tests of magnesium-alloy sheet
From Summary: "Bearing tests of AM-3S, AM-52S, and AM-C57S magnesium-alloy sheet in various thicknesses and tempers were made. Bearing yield and ultimate strengths were determined and compared for various edge distances and for various ratios of loading-pin diameter to sheet thickness. Tensile strengths were determined and ratios of average bearing yield and ultimate strength to tensile strength are given."
Date:
June 1943
Creator:
Sharp, W. H. & Moore, R. L.
System:
The UNT Digital Library
Test Data on the Shear Strength of Joints Assembled With Round-Head and Brazier-Head Rivets
Report discusses data obtained from testing shear of joints riveted with round-head and brazier-head rivets. The tightness of the rivets is also compared for one value of rivet diameter. The load-displacement curves and comparison of load at various values of permanent displacement are presented for both types of rivets.
Date:
June 1943
Creator:
Mandel, Merven W. & Schuette, Evan H.
System:
The UNT Digital Library
Effect of Exhaust Back Pressure on Engine Power
Report presenting data on the effect of exhaust back pressure on engine power for 14 aircraft engines. The data showed that the effect of exhaust back pressure on engine power varies with engine speed, range of back pressure and manifold pressure involved, and engine type. The only method of accurately determining the effect of back pressure on engine power than can currently be recommended is to test the specific engine type at the engine speed for which data are desired.
Date:
June 1943
Creator:
Pinkel, Benjamin
System:
The UNT Digital Library
The Locus of Possible Positions of a Heavy Bomber in Space After a 12-Second Time Interval
Report presenting an investigation to determine the loci of possible positions of a heavy bomber in space following a 12-second interval.
Date:
June 1943
Creator:
Mathews, Charles W. & Wood, Clotaire
System:
The UNT Digital Library
Effect of wing loading and altitude on lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel
Report presenting an investigation to determine the effects of wing loading and altitude on lateral stability and control in the free-flight tunnel. The results of flight tests of the model were correlated with calculated stability boundaries, and an effort was made to determine for each loading condition the airplane configuration that gave the best flight characteristics. Results regarding the lateral stability, lateral control, and general flight behavior are provided.
Date:
June 1943
Creator:
Campbell, John P. & Seacord, Charles L., Jr.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Effect of Yaw on Lateral-Stability Characteristics 5: Symmetrically Tapered Wing With a Circular Fuselage Having a Horizontal and a Vertical Tail
Report discussing testing to determine the effect of a horizontal tail on the lateral-stability characteristics of a high-wing, a midwing, and a low-wing monoplane. The model was created from a circular fuselage, an NACA 23012 tapered wing, and an NACA 0009 horizontal tail surface. Information about the effective aspect ratio of the tail, restoring moment of yaw, and vertical-tail effectiveness as compared to the wing position is provided.
Date:
June 1943
Creator:
Wallace, Arthur R. & Turner, Thomas R.
System:
The UNT Digital Library