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Boundary-Induced Downwash Due to Lift in a Two-Dimensional Slotted Wind Tunnel
Note presenting a solution obtained for the complete tunnel-interference flow for a lifting vortex in a two-dimensional slotted tunnel. Curves are presented for the longitudinal distribution of tunnel-induced downwash angle for various values of boundary openness parameter and various heights of the vortex above the tunnel center line.
Date:
June 1958
Creator:
Katzoff, S. & Barger, Raymond L.
System:
The UNT Digital Library
Space Heating Rates for Some Premixed Turbulent Propane-Air Flames
Note presenting measurements of space heating rate, which can yield information that is useful in characterizing turbulent combustion. For Bunsen burner flames stabilized over a field of pipe-induced turbulence, the space heating rate decreased with increasing linear flow and burner diameter and was independent of pilot conditions. Results regarding residual heat values, space conversion rate, turbulent burning velocities, and a comparison of concepts are provided.
Date:
June 1956
Creator:
Fine, Burton D. & Wagner, Paul
System:
The UNT Digital Library
The transonic characteristics of 22 rectangular, symmetrical wing models of varying aspect ratio and thickness
Report presenting an investigation to determine the aerodynamic characteristics of a series of thin, rectangular wings utilizing the transonic bump technique. Testing occurred over a range of Mach and Reynolds numbers. Lift, drag, and pitching-moment data are presented for wings of 7 different aspect ratios and NACA 63A0XX sections with 5 different thickness-to-chord ratios.
Date:
June 1955
Creator:
Nelson, Warren H. & McDevitt, John B.
System:
The UNT Digital Library
The transonic characteristics of 38 cambered rectangular wings of varying aspect ratio and thickness as determined by the transonic-bump technique
Report presenting an investigation to determine the effects of camber on the aerodynamic characteristics of a series of rectangular wings with various aspect ratios and thickness-to-chord ratios using the transonic bump method. Testing occurred over a range of Mach and Reynolds numbers. Lift, drag, and pitching moment data are presented for wings of 5 aspect ratios, NACA 63A2XX and 63A4XX sections, and 5 thickness-to-chord ratios.
Date:
June 1955
Creator:
Nelson, Warren H. & Krumm, Walter J.
System:
The UNT Digital Library
Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees
Report presenting an investigation of the aerodynamic characteristics of a four-blade rigid model propeller in the full-scale tunnel for a range of angles of attack, blade angles, and advance ratio. It included a preliminary explanation of vertical descent and a comparison with theory. Results regarding the static thrust and forward flight are provided.
Date:
June 1954
Creator:
McLemore, H. Clyde & Cannon, Michael D.
System:
The UNT Digital Library
Internal characteristics and performance of several jet deflectors at primary-nozzle pressure ratios up to 3.0
Report presenting testing of several model jet deflectors to determine the effects of design variables on their performance and operating characteristics. The deflectors were designed to be adaptable to convergent-nozzle, plug-nozzle, and ejector turbojet exhaust systems. Results regarding the swiveled-nozzle jet deflectors, auxiliary-nozzle jet deflectors, mechanical jet deflectors, and miscellaneous jet deflectors are provided.
Date:
June 1958
Creator:
McArdle, Jack G.
System:
The UNT Digital Library
Pressure Waves Generated by Addition of Heat in a Gaseous Medium
Note presenting the approximate formula of a linearized solution for the pressure field generated by a moderate rate of heat release. The analogies between the pressure waves generated by heat release and those generated by (1) mass release, (2) piston motion, or (3) a two-dimensional body in a supersonic stream are established analytically.
Date:
June 1955
Creator:
Chu, Boa-Teh
System:
The UNT Digital Library
Effect of trailing-edge thickness on lift at supersonic velocities
Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.
Date:
June 1955
Creator:
Chapman, Dean R. & Kester, Robert H.
System:
The UNT Digital Library
Studies of OH, CO, CH, and Câ‚‚ Radiation From Laminar and Turbulent Propane-Air and Ethylene-Air Flames
Note presenting an analysis of OH, CO, CH and C(sub 2) radiations from propane-air and ethylene-air flames isolated with a monochromator, and purification of the OH, CH, and C(sub 2) emitters by subtracting the unwanted CO background. The changes in intensity with changing equivalence ratio were determined for each emitter. Results regarding the variation of radiation equivalence ratio in the flame column and variation of emitter intensity with fuel-flow rate and Reynolds number are also provided.
Date:
June 1958
Creator:
Clark, Thomas P.
System:
The UNT Digital Library
Creep and Creep-Rupture Characteristics of Some Riveted and Spot-Welded Lap Joints of Aircraft Materials
Note presenting a description of equipment and test technique used in the creep testing of lap joints. Riveted aluminum-alloy joints fabricated from 75S-T6 and 24S-T3 sheet with 24S and 24S-T31 rivets were tested at 300, 400, and 500 degrees Fahrenheit. The test results showed that the creep of the riveted joints is considerably greater than the creep of the unriveted sheet although not so large that the creep of the sheet is negligible compared with that of the joints.
Date:
June 1955
Creator:
Mordfin, Leonard
System:
The UNT Digital Library
Investigation of the Effect of Impact Damage on Fatigue Strength of Jet-Engine Compressor Rotor Blades
Report presenting an investigation to determine the effect of type and location of impact damage on the fatigue strength of jet-engine compressor blades. The most serious damage was found in the nicks at the leading and trailing edges in the vicinity of the maximum-vibratory-stress section of the airfoil. Results regarding stress distribution in the blades, fatigue of the damaged blades, the fatigue test results, the correlation of reduction in strength, an analysis of the results, and testing using reworked blades are provided.
Date:
June 1956
Creator:
Kaufman, Albert & Meyer, André J., Jr.
System:
The UNT Digital Library
Study of the Subsonic Forces and Moments on an Inclined Plate of Infinite Span
Note presenting a study of existing experimental and theoretical results for an inclined flat plate of infinite span, and of the extent to which the results are indicative of those for thin airfoil sections. The study included an examination of the flow about an inclined plate, the forces on the plate, and the adequacy of theory in predicting the forces. The results indicate that there are two important ranges of angle of attack differing by the extent of flow separation on the upper surface.
Date:
June 1954
Creator:
Wick, Bradford H.
System:
The UNT Digital Library
Measurement of Heat Transfer in the Turbulent Boundary Layer on a Flat Plate in a Supersonic Flow and Comparison With Skin-Friction Results
"Local heat-transfer rates on the surface of a heated flat plate at zero incidence to an air stream flowing at Mach numbers of 1.69 and 2.27 are presented. The Reynolds number range for both Mach numbers was 1 million to 10 million. Surface temperatures were maintained near recovery temperature. It was found that the variation of heat transfer with Mach number was in agreement with previously reported variations of directly measured skin friction with Mach number on unheated bodies" (p. 1).
Date:
June 1954
Creator:
Pappas, C. C.
System:
The UNT Digital Library
Some Aspects of Fail-Safe Design of Pressurized Fuselages
"Separate investigations have dealt with the critical crack length of flat sheets or of unstiffened cylinders and with the type of rupture experienced by stiffened cylinders. These investigations are correlated, supplemented by new tests, and combined into a uniform scheme for predicting critical crack length and type of rupture in stiffened pressurized cylinders" (p. 1).
Date:
June 1957
Creator:
Kuhn, Paul & Peters, Roger W.
System:
The UNT Digital Library
Some Research Results on Sandwich Structures
"The results of compressive-buckling tests of steel sandwich plates are given, and the significant parameters which affect the strength of the plates are discussed. The various types of sandwich construction are shown to be comparable on a weight-strength basis with conventional high-strength aluminum-alloy construction" (p. 1).
Date:
June 1957
Creator:
Anderson, Melvin S. & Updegraff, Richard G.
System:
The UNT Digital Library
Theoretical and Experimental Investigations of Delta-Wing Vibrations
Note presenting the results of some theoretical and experimental investigations of delta-wing vibrations. Experimental nodal-line patterns and frequencies for a 60 degree thick-skin delta wing are shown. Comparisons of the different investigations have shown that the idealized-strucutre type of method as proposed by Levy gives excellent results for thin-skin wings provided that corrections are made for the effects of transverse shear.
Date:
June 1957
Creator:
Kruszewski, Edwin T.; Kordes, Eldon E. & Weidman, Deene J.
System:
The UNT Digital Library
Free-Falls and Parachute Descents in the Standard Atmosphere
"A detailed table of the standard equilibrium velocity and standard equilibrium time is presented for bodies falling in the standard atmosphere. This table gives the velocity at various altitudes and the time of fall from sea level to -4000 feet and from 80,000 feet to sea level. In addition to this standard table, there are given short tables and charts of an open-parachute descent and free-falls; the terminal velocity at sea level, and the variation of the weight-to-drag ratio (2w/cds)1/2 for various weight jumpers from 90 to 30 feet in open-parachute descent; and estimations of drag coefficients of silk and nylon parachutes" (p. 1).
Date:
June 1947
Creator:
Webster, A. P.
System:
The UNT Digital Library
Some effects of joint conductivity on the temperatures and thermal stresses in aerodynamically heated skin-stiffener combinations
Report presenting an analysis of temperatures and thermal stresses in typical skin-stiffener combinations of winglike structures subjected to aerodynamic heating using an electronic differential analyzer. Variations were made in aerodynamic heat-transfer parameter, in a joint conductivity parameter, and in the ratio of skin width to skin thickness. Results regarding data obtained,an illustrative example, temperature and stress ratios, and peak stress ratios and temperature-ratio drop across joint are provided.
Date:
June 1956
Creator:
Griffith, George E. & Miltonberger, Georgene H.
System:
The UNT Digital Library
Measurements of atmospheric turbulence over a wide range of wavelength for one meteorological condition
Report presenting a method for obtaining a power spectrum of gust vertical velocity over a wide range of wavelengths from simultaneous measurements in flight. It has the advantage of not involving the use of airplane transfer functions. Results regarding the measurements of velocity, including long-period and short-period measurements, and a composite spectrum over the range of frequencies are provided.
Date:
June 1956
Creator:
Crane, Harold L. & Chilton, Robert G.
System:
The UNT Digital Library
The flow past an unswept-and a swept-wing-body combination and their equivalent bodies of revolution at Mach numbers near 1.0
"Tests utilizing the schileren method of flow photography have been conducted to provide a comparison of the complete flow fields past an unswept- and a swept-wing-body combination and the flow fields past their equivalent bodies of revolution at Mach numbers around 1.0. The results indicated that the shock growth and positions on the wing-body combinations were closely reproduced in the flow past the equivalent body" (p. 1).
Date:
June 1956
Creator:
Lindsey, Walter F.
System:
The UNT Digital Library
An investigation of forward-located fixed spoilers and deflectors as gust alleviators on an unswept-wing model
Report presenting an investigation in the 300 mph 7- by 10-foot tunnel and gust tunnel to determine the static longitudinal aerodynamic characteristics an the gust-alleviation capabilities of forward-located fixed spoilers, deflectors, or a spoiler-deflector combination on a simulated transport airplane model with an unswept wing. Results regarding the static/force test, dynamic/gust-tunnel test, and short-period frequency and damping are provided.
Date:
June 1956
Creator:
Croom, Delwin R.; Shufflebarger, C. C. & Huffman, Jarrett K.
System:
The UNT Digital Library
Theoretical wave drag of shrouded airfoils and bodies
Formulas for the wave drag of shrouded symmetrical airfoils and shrouded bodies of revolution of arbitrary shape are derived by means of linearized theory. In the case of the airfoils, the shroud consists of flat plates and for the bodies of revolution the shroud is a cylindrical shell. The results obtained hold for a Mach number range dependent on the geometry of the configuration. Expressions are also given for determining a class of body shapes for which the wave drag is theoretically zero.
Date:
June 1956
Creator:
Byrd, Paul F.
System:
The UNT Digital Library
Flow characteristics over a lifting wedge of finite aspect ratio with attached and detached shock waves at a Mach number of 1.40
From Summary: "A series of schileren photographs and pressure distributions are presented which show the effects of transition from an attached to a detached shock at the leading edge of a finite-span, 8.2 degree wedge as the angle of attack is increased. These data were obtained in the Langley 4- by 4-foot supersonic tunnel at a Mach number of 1.40."
Date:
June 1952
Creator:
Hilton, John H., Jr.
System:
The UNT Digital Library
Effectiveness of Ceramic Coatings in Reducing Corrosion of Five Heat-Resistant Alloys by Lead-Bromide Vapors
Note presenting testing to determine whether lead compounds in the combustion products of high-octane fuel are a contributing factor in causing failures of the heat-resistant alloy parts in aircraft exhaust systems. To obtain answers for five heat-resistant alloys, a test was devised in which the alloy specimens in an uncoated condition, in a preoxidized condition, and with three different ceramic coatings were exposed for 6 hours to lead-containing vapors in an air atmosphere at 3 different temperatures.
Date:
June 1951
Creator:
Moore, Dwight G. & Mason, Mary A.
System:
The UNT Digital Library