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The Calculation of Span Load Distributions of Swept-Back Wings
"Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9" (p. 1).
Date:
December 1941
Creator:
Mutterperl, William
System:
The UNT Digital Library
Compressive Strength of 24S-T Aluminum-Alloy Flat Panels With Longitudinal Formed Hat-Section Stiffeners
"Results are presented for a part of a test program on 24S-T aluminum alloy flat compression panels with longitudinal formed hat-section stiffeners. This part of the program is concerned with panels in which the thickness of the stiffener materials is 0.625 times the skin thickness. The results, presented in tabular and graphical form, show the effect of the relative dimensions of the panel on the buckling stress and the average stress at maximum load" (p. 1).
Date:
December 1946
Creator:
Schuette, Evan H.; Barab, Saul & McCracken, Howard L.
System:
The UNT Digital Library
An analysis of the airspeeds and normal accelerations of Boeing B-247 and B-247D airplanes in commercial transport operation
From Introduction: "The results of analyses of V-G data given in references 1 to 5 have shown that the flight loads of airplanes operated in commercial transport service are influenced by operating speeds and by forecasting and dispatching practices as reflected in differences between operations during the prewar and wartime periods. The available data are summarized and the flight results are compared with the results of analyses made in references 1 to 5."
Date:
December 1948
Creator:
Walker, Walter G. & Hadlock, Ivan K.
System:
The UNT Digital Library
Recommendations for numerical solution of reinforced-panel and fuselage-ring problems
Report presenting procedures for solving the equations of equilibrium of reinforced panels and isolated fuselage rings as represented by the external loads and operations table established according to Southwell's method. By using these equations, the stress distribution can be easily determined.
Date:
December 1948
Creator:
Hoff, N. J. & Libby, Paul A.
System:
The UNT Digital Library
Notes and Tables for Use in the Analysis of Supersonic Flow
Paper presenting a compilation of formulas, tables, and curves that have been found to be useful in the analysis of supersonic wind-tunnel data.
Date:
December 1947
Creator:
The Staff of the Ames 1- by 3-foot Supersonic Wind-Tunnel Section
System:
The UNT Digital Library
Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys
Note presenting a method by which the total temperature of the gases at the combustion-chamber outlet of a ramjet engine may be determined from the loss in total pressure measured across the combustion chamber. Values of total-temperature ratio across the combustion chamber of a 20-inch ram jet were obtained in the altitude wind tunnel over a range of pressure altitudes.
Date:
December 1951
Creator:
Pinkel, I. Irving
System:
The UNT Digital Library
Ceramic Coatings for Prevention of Carbon Absorption in Four Heat-Resistant Alloys
Note presenting an investigation of three ceramic coatings applied to four heat-resistant alloys that are tested for effectiveness in preventing carbon absorption under strongly carburizing conditions (box carburizing).
Date:
December 1951
Creator:
Pitts, Joseph W. & Moore, Dwight G.
System:
The UNT Digital Library
Effect of changing manifold pressure, exhaust pressure, and valve timing on the air capacity and output of a four-stroke engine operated with inlet valves of various diameters and lifts
Report presenting a series of tests made with a CFR engine to determine the effect of inlet-valve capacity, inlet and exhaust pressure, and valve timing on the volumetric efficiency at various speeds. Three combinations of inlet and exhaust pressures and seven valve-timing arrangements were used.
Date:
December 1947
Creator:
Livengood, James C. & Eppes, James V. D.
System:
The UNT Digital Library
Relation Between Inflammables and Ignition Sources in Aircraft Environments
From Summary: "A literature survey was conducted to determine the relation between aircraft ignition sources and inflammables. Available literature applicable to the problem of aircraft fire hazards is analyzed and discussed herein. Data pertaining to the effect of many variables on ignition temperatures, minimum ignition pressures, and minimum spark-ignition energies of inflammables, quenching distances of electrode configurations, and size of openings incapable of flame propagation are presented and discussed."
Date:
December 1950
Creator:
Scull, Wilfred E.
System:
The UNT Digital Library
Critical Combinations of Bending, Shear, and Transverse Compressive Stresses for Buckling of Infinitely Long Flat Plates
"Three-dimensional interaction surfaces are presented for the computation of elastic buckling stresses for an infinitely long flat plate subjected to combinations of bending, shear, and transverse compression in its plane - a loading approximating that occurring in a shear web. Surfaces are presented for two sets of edge conditions: both edges simply supported and lower edge simply supported, upper edge clamped. Present results are in good agreement with data for one-load and two-load limiting cases previously published" (p. 1).
Date:
December 1951
Creator:
Johnson, Aldie E., Jr. & Buchert, Kenneth P.
System:
The UNT Digital Library
An investigation at subsonic speeds of several modifications to the leading-edge region of the NACA 64A010 airfoil section designed to increase maximum lift
Report presenting three modifications to the leading-edge region of the NACA 64A010 airfoil section, which were designed and tested two-dimensionally at both low and high subsonic speeds. The modifications increased the low-speed maximum lift coefficient of the symmetrical reference section, largely by increasing the angle of attack at which stall occurred.
Date:
December 1956
Creator:
Maki, Ralph L. & Hunton, Lynn W.
System:
The UNT Digital Library
Mechanical and Corrosion Tests of Spot-Welded Aluminum Alloys
Note presenting an investigation to determine the effect of spot-weld quality on the corrosion behavior of panels fabricated from alclad 24S-T3, 24S-T3, R-301-T6 of 0.020-inch thickness. The preparation and examination of each of the specimens is described. Results regarding effect of exposure on weld shear strength, effect of exposure on normal tensile strength of welds, and a metallographic examination of spot welds are provided.
Date:
December 1951
Creator:
Reinhart, Fred M.; Hess, W. F.; Wyant, R. A.; Winsor, F. J. & Nash, R. R.
System:
The UNT Digital Library
Wind-tunnel investigation of jet-augmented flaps on a rectangular wing to high momentum coefficients
Report presenting an investigation of jet flaps in the 300 mph 7- by 10-foot tunnel on an unswept, untapered wing with an aspect ratio of 8.4 and a thickness of 16.7 percent. Results regarding jet flap, jet-augmented trim flap, jet-augmented plain flap, and estimated thrust required for steady flight of an airplane with the jet-flap system are provided.
Date:
December 1956
Creator:
Lockwood, Vernard E.; Riebe, John M. & Turner, Thomas R.
System:
The UNT Digital Library
Method for Calculating Effects of Dissociation on Flow Variables in the Relaxation Zone Behind Normal Shock Waves
Report presenting generalized expressions and charts which depend on the shock Mach number, initial state of the gas, and an enthalpy parameter for the temperature, pressure, density, and flow velocity behind a shock wave.
Date:
December 1956
Creator:
Evans, John S.
System:
The UNT Digital Library
A Survey of Background and Aircraft Noise in Communities Near Airports
Note presenting the results of a survey of background and aircraft noise levels in residential communities in eight cities with major airports. The measurements were made in areas up to 12 miles away from the airports and were located in regularly used flight paths. The results indicated that there is a range of more than 20 decibels in the average background noise in the 180 areas included in the survey.
Date:
December 1954
Creator:
Stevens, K. N.
System:
The UNT Digital Library
Experimental determination of the range of applicability of the transonic area rule for wings of triangular plan form
From Summary: "Experimental measurements have been made of the zero-lift drag rise at transonic speeds of a family of triangular plan form wings of varying thickness and aspect ratio mounted on a cylindrical body. Together with the transonic similarity parameters, the results of the tests are used to define the range of applicability of the transonic area rule for wings of triangular plan form. The significance of the test results is discussed."
Date:
December 1956
Creator:
Page, William A.
System:
The UNT Digital Library
Wind-tunnel investigation at low speeds to determine the effect of aspect ratio and end plates on a rectangular wing with jet flaps deflected 85 degrees
Report presenting a wind-tunnel investigation at low speeds to determine the effect of aspect ratio and end plates on the aerodynamic characteristics of an unswept and untapered wing equipped with jet flaps deflected 85 degrees and operating with momentum coefficients as high as 17.5.
Date:
December 1956
Creator:
Lowry, John G. & Vogler, Raymond D.
System:
The UNT Digital Library
Theoretical calculation of the power spectra of the rolling and yawing moments on a wing in random turbulence
Report presenting calculations of the correlation functions and power spectra of the rolling and yawing moments on an airplane wing due to the three components of continuous random turbulence. Specific numerical calculations are made for a pair of correlation functions given by simple analytic expressions which fit available experimental data.
Date:
December 1956
Creator:
Eggleston, John M. & Diederich, Franklin W.
System:
The UNT Digital Library
Laminar Boundary Layer With Heat Transfer on a Cone at Angle of Attack in a Supersonic Stream
Note presenting the equations of the compressible laminar boundary layer for the windward streamline in the plane of symmetry of a yawed cone. Solutions are obtained for both insulated and cooled surfaces. The heat-transfer rate to this most windward streamline increases significantly with angle of attack.
Date:
December 1957
Creator:
Reshotko, Eli
System:
The UNT Digital Library
One-Dimensional, Compressible, Viscous Flow Relations Applicable to Flow in a Ducted Helicopter Blade
Report presenting one-dimensional, steady-state, compressible, viscous flow relations which permit the determination of flow conditions at any radial position in a ducted helicopter blade. The relations are required for estimating the performance of proposed helicopter jet-propulsion systems which involve ducting air or gases through the blade from root to tip.
Date:
December 1953
Creator:
Henry, John R.
System:
The UNT Digital Library
A Fundamental Investigation of Fretting Corrosion
Note presenting a summary of all phases of an investigation of fretting corrosion that has been conducted over a period of several years. Part I describes a test machine for measuring fretting damage under controlled experimental conditions. Part II presents data for mild steel fretted against itself, with a number of characteristics taken into consideration. Part III suggest a mechanism for the fretting process.
Date:
December 1953
Creator:
Uhlig, H. H.; Feng, I. Ming; Tierney, W. D. & McClellan, A.
System:
The UNT Digital Library
Operating Characteristics of an Acceleration Restrictor as Determined by Means of a Simulator
Note presenting the operating characteristics of an acceleration restrictor which limits the normal acceleration of an airplane in maneuvers determined from tests on a simulator. The simulator consisted of a control stick geared to a magnetic brake unit and an analog computer which simulated the dynamic characteristics of the airplane.
Date:
December 1954
Creator:
Assadourian, Arthur
System:
The UNT Digital Library
Analytical determination of the mechanism of an airplane spin recovery with different applied yawing moments by use of rotary-balance data
From Introduction: "These aerodynamic data were used previously in an analytical investigation of a spin recovery by rudder reversal, the results of which have been published in reference 2. Because of certain discrepancies in the rotary-balance data similar to those discussed in reference 3, some modifications were made to the aerodynamic data used in calculating the results in reference 2 and also the results in this paper; these discrepancies and modifications are discussed in detail herein."
Date:
December 1954
Creator:
Burk, Sanger M., Jr.
System:
The UNT Digital Library
Approximate effect of leading-edge thickness, incidence angle, and inlet mach number on inlet losses for high-solidity cascades of low cambered blades
Report presenting an approximate, theoretical analysis of the inlet or induction losses due to subsonic flow into a high-solidity cascade of finite thickness blades at incidence angle. Results indicated that the losses can become considerable for large deviations from the design incidence such as compressor off-design operating conditions. Results regarding the computational results, significance of assumptions and limitations, comparison of theoretical approximation with actual compressor results, and applicability of the results are provided.
Date:
December 1954
Creator:
Wright, Linwood C.
System:
The UNT Digital Library