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Statistical Study of Aircraft Icing Probabilities at the 700- and 500- Millibar Levels over Ocean Areas in the Northern Hemisphere
From Summary: "A statistical study is made of icing data reported from weather reconnaissance aircraft flown by Air Weather Service (USAF). The weather missions studied were flown at fixed flight levels of 500 millibars (18,000 ft) and 700 millibars (10,000 ft) over wide areas of the Pacific, Atlantic, and Arctic Oceans. This report is presented as part of a program conducted by the NACA to obtain extensive icing statistics relevant to aircraft design and operation. The thousands of in-flight observations recorded over a 2- to 4-year period provide reliable statistics on icing encounters for the specific areas, altitudes, and seasons included in the data."
Date:
May 1957
Creator:
Perkins, Porter J.; Lewis, William & Mulholland, Donald R.
System:
The UNT Digital Library
British Certificates of Airworthiness
This report details the rules and regulations for obtaining a British airworthiness certificate. Aircraft loading and construction are especially important.
Date:
May 1921
Creator:
unknown
System:
The UNT Digital Library
Droplet Impingement and Ingestion by Supersonic Nose Inlet in Subsonic Tunnel Conditions
"The amount of water in cloud droplet form ingested by a full-scale supersonic nose inlet with conical centerbody was measured in the NACA Lewis icing tunnel. Local and total water impingement rates on the cowl and centerbody surfaces were also obtained. All measurements were made with a dye-tracer technique" (p. 1).
Date:
May 1958
Creator:
Gelder, Thomas F.
System:
The UNT Digital Library
Notes on the Theory of the Accelerometer
Report discusses several types of accelerometers and how they function. Methods for reducing error and determining the source of the error, including the best placement for the device, are included.
Date:
May 1920
Creator:
Warner, E. P.
System:
The UNT Digital Library
The Problem of the Helicopter
Report discussing some of the issues regarding the design and operation of helicopters and the theoretical basis behind them. Some particular issues covered include propeller blade design, helicopters in forced descent, horizontal travel, and stability and control.
Date:
May 1920
Creator:
Warner, E. P.
System:
The UNT Digital Library
Airplane Superchargers
Discussed here are the principles and operation of aircraft engine superchargers used to maintain and increase engine power as aircraft encounter decreases in the density of air as altitude rises. Details are given on the design and operation of the centrifugal compressors. A method is given for calculating the amount of power needed to drive a compressor. The effects of the use of a compressor on fuel system operation and design are discussed. Several specific superchargers that were in operation are described.
Date:
May 1921
Creator:
Noack, W. G.
System:
The UNT Digital Library
On a New Type of Wind Tunnel
Discussed here is a new type of wind tunnel, its advantages, the difficulties attendant upon its use, and the special methods required for its operation. The main difference between the new type of wind tunnel and the ones now in operation is the use of a different fluid. The idea is to diminish the effect of viscosity.
Date:
May 1921
Creator:
Munk, Max
System:
The UNT Digital Library
Sylphon diaphragms : a method for predicting their performance for purposes of instrument design
Here, the purpose is to show that the characteristic performance of a syphon diaphragm can be predicted from a knowledge of its stiffness and of its dimensions. The proof is based on a mathematical analysis of this type of diaphragm, together with enough experimental data to prove the validity of the assumptions and the sufficiency of the analysis. Equations are developed for the performance of syphons under various conditions of loading, both for concentrated loads and for hydrostatic pressure.
Date:
May 1922
Creator:
Eaton, H. N. & Keulegan, G. H.
System:
The UNT Digital Library
Notes on Propeller Design III: The Aerodynamical Equations of the Propeller Blade Elements
The air flow and the air force created by all elements of the propeller blades lying in a ring located between two concentric circles around the propeller axis are independent of what happens in other rings.
Date:
May 1922
Creator:
Munk, Max M.
System:
The UNT Digital Library
Notes on Propeller Design 4: General Proceeding in Design
The choice of the numbers of revolutions and of the diameter, the distribution of thrust, and the values of the constants in the aerodynamical equations of the propeller are discussed.
Date:
May 1922
Creator:
Munk, Max M.
System:
The UNT Digital Library
N.A.C.A. control position recorder
Report discussing a new instrument is described which is capable of simultaneously recording the position of the three controls of an airplane. The records are taken photographically on a standard N.A.C.A. film drum and the instrument can be quickly installed in any airplane.
Date:
May 1922
Creator:
Norton, F. H.
System:
The UNT Digital Library
Notes on the Design of Latticed Columns Subject to Lateral Loads
"No rational column formula has yet been developed which gives results which are sufficiently precise for the design of airplane members, and consequently it is necessary to fall back upon experimental testing. In order to derive the maximum benefit from experiments, however, it is necessary that the experiments be guided by theory. It is the object here to modify existing formulae that may be obtained with a minimum number of tests" (p. 1).
Date:
May 1922
Creator:
McCarthy, Charles J.
System:
The UNT Digital Library
Airplane Performance as Influenced by the Use of a Supercharged Engine
"The question of the influence of a supercharged engine on airplane performance is treated here in a first approximation, but one that gives an exact idea of the advantage of supercharging. Considered here is an airplane that climbs first with an ordinary engine, not supercharged, and afterwards climbs with a supercharged engine. The aim is to find the difference of the ceilings reached in the two cases" (p. 1).
Date:
May 1920
Creator:
de Bothezat, George
System:
The UNT Digital Library
Relation of Rib Spacing to Stress in Wing Planes
The stress relations to the fabric and the rib consequent upon a change of spacing between ribs in a wing plane are discussed. Considering the wing plane as a static structure, and ignoring the question of aerodynamic efficiency, it appears that the unit stress in the rib and fabric will remain constant for constant p if the linear dimensions of both rib and fabric are increased alike, viz., if wing and fabric remain geometrically similar. Since the bulge and the structural dimensions remain geometrically similar, the whole distended plane remains so, and hence should have the same pressure distribution and efficiency.
Date:
May 1920
Creator:
Zahm, A. F.
System:
The UNT Digital Library
Further Experimental Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil
Note presenting a low-turbulence wind-tunnel investigation of an NACA 64A010 airfoil with a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of area suction. This report primarily deals with additional tests of the same airfoil model equipped with a porous skin of lower porosity.
Date:
May 1950
Creator:
Braslow, Albert L. & Visconti, Fioravante
System:
The UNT Digital Library
Fabrication and Properties of Hot-Pressed Molybdenum Disilicide
Report presenting an investigation of hot-pressed molbdenum disilicide bodies produced by industrial processes at a temperature of 2950 degrees and a pressure of 3000 pounds per square inch. Results regarding the short-time tensile strength, stress-rupture data, compression strength, air-corrosion resistance, hardness, coefficient of linear thermal expansion, thermal conductivity, and density are provided.
Date:
May 26, 1950
Creator:
Long, Roger A.
System:
The UNT Digital Library
Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results
"A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases" (p. 1).
Date:
May 21, 1952
Creator:
Scadron, Marvin D.
System:
The UNT Digital Library
Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Tail Attached to a Segment of the Foreshortened Body
"An investigation has been made of a partial-span model of the tail surface designed for use on the Hughes Falcon (MX-904) missile to determine the aerodynamic characteristics of the tail and elevator including elevator hinge moment. Data obtained at Mach numbers of 1.62 and 1.96 in the Langley 9- by 12-inch supersonic blowdown tunnel are presented for the condition where the tail was attached to a segment of the foreshortened body" (p. 1).
Date:
May 4, 1950
Creator:
Conner, D. William & Guy, Lawrence D.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Aerodynamic Characteristics of a 0.07-Scale Model of the North American MX-770 Missile
Report presenting the results of an investigation at supersonic speeds to determine the aerodynamic characteristics of a model of the North American MX-770 missile at several designated Mach numbers. No analysis is provided. Information about the longitudinal aerodynamic characteristics with trimmer and elevon deflected and lateral aerodynamic characteristics are described.
Date:
May 7, 1952
Creator:
Pfyl, Frank A.
System:
The UNT Digital Library
Experimental Investigation of Extreme Internal Flow Turning at the Cowl Lip of an Axisymetric Inlet at a Mach Number of 2.95
Memorandum presenting an experimental investigation of the pressure-recovery performance of a fixed-geometry, two-cone, two-drag inlet at Mach number 2.95. Low drag was achieved by use of an internally cylindrical cowl with rapid flow turning that was within 4 degrees of the wedge angle for shock detachment. Results regarding the inlet performance and evaluation of inlet performance are provided.
Date:
May 13, 1958
Creator:
Weston, Kenneth C. & Kowalski, Kenneth L.
System:
The UNT Digital Library
Performance at High Temperatures and Pressures of an Annular Turbojet Combustor Having Articulated Liner Walls
Report discussing the performance of an experimental quarter-sector annular combustor at conditions simulating supersonic flight of a cooled-turbine engine, as well as 20 different modification to the design. The final configuration was found to show no structural failures and little or no warping of liner parts after 40 hours of operation.
Date:
May 10, 1957
Creator:
McCafferty, Richard J.; Wear, Jerrold D. & Cook, William P.
System:
The UNT Digital Library
Analysis of Circular Shell-Supported Frames
From Summary: "This paper deals with the single problem if circular shell-supported frames subjected to concentrated loadings. A mathematical attack is developed and presented in the form of nondimensional-coefficient curves."
Date:
May 1944
Creator:
Wignot, J. E.; Combs, Henry & Ensrud, A. F.
System:
The UNT Digital Library
The Effect of Wind Tunnel Turbulence Upon the Forces Measured on Models
These tests were undertaken to find the effect of turbulence in the air stream upon the lift and drag forces measured on models in the four-foot wind tunnel at the Massachusetts Institute of Technology. Maximum lifts and minimum drags were measured on Gottingen-387 and R.A.F.-15 airfoils, minimum drag on a streamlined strut, and the static pressure gradients for different conditions of turbulence were investigated. The results show that the scale of the turbulence (as defined in this report) has a marked effect upon the measured forces on models tested in the tunnel as well as on the pressure gradient, and it is recommended that further investigation of the phenomena be made with the aid of smoke and small wind vanes.
Date:
May 1924
Creator:
LePage, W. L. & Nichols, J. T.
System:
The UNT Digital Library
Note on the Pressure Distribution Over the Hull of Elongated Airships With Circular Cross Section
"This note, prepared for the National Advisory Committee for Aeronautics, contains the demonstration that the pressure around the circular cross section of an elongated airship, plotted against the diameter of symmetry, can be expected to be represented by a straight line" (p. 1).
Date:
May 1924
Creator:
Munk, Max M.
System:
The UNT Digital Library