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Charts for Determining Preliminary Values of Span-Load, Shear, Bending-Moment, and Accumulated-Torque Distributions of Swept Wings of Various Taper Ratios
Contains charts for use in determining preliminary values of the spanwise-load, shear, bending-moment, and accumulated-torque distributions of swept wings. The charts are based on strip theory and include four aerodynamic-load distributions, two section-moment distributions, and two inertia-load distributions. The taper ratios considered cover the range from 1.0 to 0 and the results are applicable to any angle of sweep.
Date:
July 6, 1948
Creator:
Wollner, Bertram C.
System:
The UNT Digital Library
Conversations regarding RW
None
Date:
July 6, 1948
Creator:
Gast, P. F.
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine. 2 - Operational Characteristics
From Summary: "An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational characteristics of an axial flow-type turbojet engine with a 4000-pound-thrust rating over a range of pressure altitudes from 5,000 to 50,000 feet, ram pressure ratios from 1.00 to 1.86, and temperatures from 60 deg to -50 deg F. The low-flow (standard) compressor with which the engine was originally equipped was replaced by a high-flow compressor for part of the investigation. The effects of altitude and airspeed on such operating characteristics as operating range, stability of combustion, acceleration, starting, operation of fuel-control systems, and bearing cooling were investigated."
Date:
August 6, 1948
Creator:
Fleming, William A.
System:
The UNT Digital Library
Cooperation with US Geological Survey
This is a reference made to a memorandum about the cooperation between the Hanford Site and the US Geological Survey. The US Geological Survey was at the site to work with Hanford on geological problems the site was having. They worked together to locate the water supply wells of the site which would be coordinated with the drilling program. They also worked together on the possible contamination to the 300 and 3000 area wells. (MB)
Date:
August 6, 1948
Creator:
unknown
System:
The UNT Digital Library
Investigation of X24C-2 10-Stage Axial-Flow Compressor 3 - Surge Characteristics
Compressor operation at low air flows for a given speed is limited by unstable flow conditions, commonly called surge. An investigation of surge in centrifugal compressors (reference 1) showed that the pulsation of pressures and velocities occurred when the slope of the compressor characteristic curve was positive and that the magnitude and frequency, as well as the incidence of surge, depended on the capacity and resistance of the total system. Although the theory presented in reference 1 is applicable to axial-floe compressors, little experimental information is available on the surge characteristics of the individual stages of axial-flow compressors, or on the variation of the surge characteristics with operating conditions.
Date:
August 6, 1948
Creator:
Buckner, Howard A., Jr. & Downing, Richard M.
System:
The UNT Digital Library
Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine 5 - Combustion-Chamber Characterisitcs
"An investigation to determine the performance and operational characteristics of an axial-flow gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet ram-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected horsepower" (p. 1).
Date:
August 6, 1948
Creator:
Geisenheyner, Robert M. & Berdysz, Joseph J.
System:
The UNT Digital Library
Preliminary Results of Natural Icing of an Axial-Flow Turbojet Engine
Memorandum presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Tail-pipe temperature increased from 761 to 1065 degrees Fahrenheit and the jet thrust decreased from 1234 to 910 pounds during a period of 45 minutes in icing. No general conclusions can be reached from the data because the icing condition was relatively light.
Date:
August 6, 1948
Creator:
Acker, Loren W.
System:
The UNT Digital Library
Preliminary results of natural icing of an axial-flow turbojet engine
Report presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Results regarding the tail-pipe temperature, engine jet thrust, and characteristics of ice formation are provided. No general conclusions can be reached from the data because the icing condition was relatively light.
Date:
August 6, 1948
Creator:
Acker, Loren W.
System:
The UNT Digital Library
Preliminary Results of Nene Ii Engine Altitude-Chamber Performance Investigation 3 - Altitude Performance Using 18.00-Inch-Diameter Jet Nozzle
"An investigation is being conducted to determine the altitude performance characteristics of the Nene II engine and its components. The present paper presents the preliminary results obtained using jet nozzle 18.00 inches in diameter, with an area equal to 92.2 percent of the area of the standard jet nozzle for this engine. The experimental results presented are for conditions simulating altitudes from 20,000 to 60,000 feet and ram-pressure ratios from 1.1 to 3.5" (p. 1).
Date:
August 6, 1948
Creator:
Grey, Ralph E. & Brightwell, Virginia L.
System:
The UNT Digital Library
The effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing
"An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing. Longitudinal and lateral stability characteristics were obtained for the model with and without tail surfaces" (p .1).
Date:
December 6, 1948
Creator:
Spearman, M. Leroy & Becht, Robert E.
System:
The UNT Digital Library
Initial Experiments on Flutter of Unswept Cantilever Wings at Mach Number 1.3
Report presenting the results of a preliminary experimental flutter investigation of widely different unswept cantilever wings at Mach number 1.3. Wings with a variety of mass-density parameters, center-of-gravity positions, and elastic-axis positions were tested.
Date:
January 6, 1949
Creator:
Tuovila, W. J.; Baker, John E. & Regier, Arthur A.
System:
The UNT Digital Library
Corrosion Tests on Carboloy in Redox Process Solutions
Introduction: Static, total immersion corrosion tests were carried out at room temperatures with Carboloy grades 44-A, 78, 907, X-3119-A and X-3119-B in Redox process solutions (ANL, June 1, 1949 Flowsheet) 1AX, 1AF, and 1AS.
Date:
April 6, 1949
Creator:
Koenig, W. W.
System:
The UNT Digital Library
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25
Testing was performed at Mach number 1.53 with a wing-fuselage combination with a wing with 63 degrees leading-edge sweep, an aspect ratio of 3.46, and a taper ratio of 0.25. The wing had an NACA 64A005 thickness distribution parallel to the plane of symmetry and was cambered and twisted. Results regarding the comparison of lift, drag, and pitching-moment characteristics of WF-63c and WF-63, effects of sweep, and effects of Reynolds number are provided.
Date:
May 6, 1949
Creator:
Madden, Robert T.
System:
The UNT Digital Library
Events of importance for week ending May 4, 1949
This report details events of importance reported by the Hanford Operations Office for the week ending May 4, 1949.
Date:
May 6, 1949
Creator:
Schlemmer, F. C.
System:
The UNT Digital Library
Pressure-Distribution Data for the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers
"Pressure-distribution data of the NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils have been analyzed to determine the effects of increasing the trailing-edge angle from 9 to 14 degrees. The primary effect of increasing the trailing-edge angle was to decrease the loading over the rear portion of the airfoil under lifting conditions. The differences in trailing-edge load increased with Mach number and lift coefficient" (p. 1).
Date:
May 6, 1949
Creator:
Humphreys, Milton D.
System:
The UNT Digital Library
The Effect of Blade-Section Thickness Ratios on the Aerodynamic Characteristics of Related Full-Scale Propellers at Mach Numbers Up to 0.65
Report discussing an investigation of two full-scale NACA propellers at a range of blade angles and at speeds of up to 500 miles per hour. The results are compared to previous investigations of five NACA propellers to evaluate the effects of blade-section thickness ratios on propeller characteristics.
Date:
June 6, 1949
Creator:
Maynard, Julian D. & Steinberg, Seymour
System:
The UNT Digital Library
Investigation of downwash and wake characteristics at a Mach number of 1.53 2: triangular wing
Report presenting the results of an experimental investigation of the downwash and wake characteristics behind a triangular plan-form wing in a supersonic stream. Measurements were made of the variation of downwash angle with angle of attack at several positions within the induced flow field. Results regarding the spanwise variation of the induced stream angle, rate of change of downwash at zero lift, variation of downwash with angle of attack, and wake are provided.
Date:
June 6, 1949
Creator:
Perkins, Edward W. & Canning, Thomas N.
System:
The UNT Digital Library
Material balance flowsheet Redox Production plant
The attached material balance flowsheet for the proposed Redox Production plant is based on the two chemical flowsheets submitted by R.B. Richards of the Technical Division in HW 13,320 (INDC-3130) and HW 13,452 (INDC 3176). Production rates for the plant have been assumed as 2.5 short tone U per day (including a maximum of 0.75 short tons of U from stored Bi PO{sub 4} waste) and 19 kg. Pu per month (633 gms/day) as established by the Redox Committee. The flowsheets for preparation of solvent extraction feed from Bi PO{sub 4} waste, as well as the waste treatment systems will be covered in a future document.
Date:
June 6, 1949
Creator:
Tomlinson, R.E.
System:
The UNT Digital Library
Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine 2 - Performance of Inlet Guide Vanes as Separate Component
"The inlet guide vanes for the supersonic compressor of the XJ55-FF-1 engine were studied as a separate component in order to determine the performance prior to installation in the compressor test rig. Turning angles approached design values, and increased approximately to through the inlet Mach number range from 0.30 to choke. A sharp break in turning angle was experienced when the choke condition was reached" (p. 1).
Date:
June 6, 1949
Creator:
Graham, Robert C. & Tysl, Edward R.
System:
The UNT Digital Library
Performance of J33 turbojet engine with shaft-power extraction 3: turbine performance
From Summary: "The performance of the turbine component of a J33 turbojet engine was determined over a range of turbine speeds from 8000 to 11,500 rpm.Turbine-inlet temperature was varied from the minimum required to drive the compressor to a maximum of approximately 2000 degrees R at each of several intermediate turbine speeds. Data are presented that show the horsepower developed by the turbine per pound of gas flow."
Date:
June 6, 1949
Creator:
Huppert, M. C. & Nettles, J. C.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Low-Speed Static Stability and Control Characteristics of a Model of Bell MX-776
An investigation has been made in the Langley stability tunnel to determine the low-speed static stability and control characteristics of a model of the Bell MX-776. The results of the investigation indicated that the basic model configuration was longitudinally stable in the angle-of-attack range from about -16 deg. to 16 deg. but that the stability was a minimum near O deg angle of attack. The data indicated an aerodynamic-center position about 0.64 body diameters behind the center of gravity at low angles of attack. Reduction in the size of the front horizontal fins increased the longitudinal stability. With 20 percent of the span of the normal front horizontal fins cut off the aerodynamic center was about 1.04 body diameters behind the center of gravity, and with front horizontal fins having the same area as the front vertical fins, the aerodynamic center was 2.26 body diameters behind the center of gravity (at low angles of attack).
Date:
July 6, 1949
Creator:
Queijo, M. J. & Michael, W. H., Jr.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic-bump method
From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuelage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date:
September 6, 1949
Creator:
King, Thomas J., Jr. & Myers, Boyd C., II
System:
The UNT Digital Library
Two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil section with leading-edge and trailing-edge high-lift devices deflected in combination
Report presenting a two-dimensional wind-tunnel investigation of a 6-percent-thick symmetrical circular-arc airfoil with leading-edge and trailing-edge high-lift devices. The purpose of the investigation was to determine the effects on maximum section lift coefficient of different leading-edge slats and drooped-nose flaps when used in combination with a plain trailing-edge flap. Results regarding slat configuration, drooped-nose-flap configurations, and a comparison of slat and drooped-nose-flap configurations are provided.
Date:
September 6, 1949
Creator:
Nuber, Robert J. & Cheesman, Gail A.
System:
The UNT Digital Library
An Analysis of Airspeeds Attained by a Douglas DC-4 Airplane in Commercial Operations During the Early Months of 1947
Report presenting airspeed and altitude data for nonscheduled cargo operations of a Douglas DC-4 airplane between Seattle, Washington and Alaska during February and March of 1947 to determine the probability of reaching or exceeding given values of airspeed and Mach number. The total probability of exceeding a placard never-exceed speed of 266 mph depends primarily on exceeding the speed in descent. The probability was found to be about once in 100 hours of descent or once in 1000 hours of general flying time.
Date:
October 6, 1949
Creator:
Steiner, Roy
System:
The UNT Digital Library