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Oscillating pressures near a static pusher propeller at tip Mach numbers up to 1.20 with special reference to the effects of the presence of the wing
Report presenting measurements of free-space oscillating pressures near a static propeller in the region where a wing might be located are presented for a range of tip Mach numbers and the results are compared with available theory. The radial pressure distributions vary as a function of axial distance and order of the harmonic. Results regarding free-space pressures and wing pressures are provided.
Date:
July 1954
Creator:
Hubbard, Harvey H. & Lassiter, Leslie W.
System:
The UNT Digital Library
Shock-turbulence interaction and the generation of noise
Report presenting the interaction of a convected field of turbulence with a shock wave, which has been analyzed to yield the modified turbulence, entropy spottiness, and noise generated downstream of the shock. The results in this report are applicable quantitatively to flow in ducts or channels containing normal shocks.
Date:
July 1954
Creator:
Ribner, H. S.
System:
The UNT Digital Library
Effects of Nose Shape and Spray Control Strips on Emergence and Planing Spray of Hydro-Ski Models
Report presenting the emergence- and planing-spray characteristics of flat-bottom surfaces representing hydro-skis with various bow shapes and deflectors. The most favorable emergence spray was obtained with a bow of triangular plan form and sharp profile. Results regarding practical design considerations are also provided.
Date:
July 1958
Creator:
McGehee, John R.
System:
The UNT Digital Library
Estimation of Forces and Moments Due to Rolling for Several Slender-Tail Configurations at Supersonic Speeds
Note presenting the velocity potentials, span loadings, and corresponding force and moment derivatives for a number of slender-tail arrangements performing a steady rolling motion at supersonic speeds. The method of analysis is based on an application of conformal-transformation techniques.
Date:
July 1953
Creator:
Bobbitt, Percy J. & Malvestuto, Frank S., Jr.
System:
The UNT Digital Library
Experimental investigation of temperature recovery factors on a 10 degree cone at angle of attack at a Mach number of 3.12
Report presenting temperature recovery factors on a thin-walled, metal, 10 degree included angle cone at a Mach number of 3.12 over a range of angles of attack and Reynolds numbers per foot. An increase in angle of attack was found to increase the equilibrium surface temperatures in the laminar and turbulent boundary-layer regions.
Date:
July 1954
Creator:
Jack, John R. & Moskowitz, Barry
System:
The UNT Digital Library
Compressive Strength and Creep of 17-7 PH Stainless-Steel Plates at Elevated Temperatures
Note presenting compressive strength test results from room temperature to 1000 degrees Fahrneheit and compressive creep test results from 700 to 1000 degrees Fahrenheit for plates of 17-7 PH stainless steel, Condition TH 1050, which were edge-supported in V-groove fixtures. The combinations of average stress, temperature, and time that produce given amounts of creep strain or failure are shown on master curves which facilitate interpolation of the test results.
Date:
July 1958
Creator:
Stein, Bland A.
System:
The UNT Digital Library
The Effects of Compressibility on the Upwash at the Propeller Planes of a Four-Engine Tractor Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10
Report presenting an investigation in which upflow angles were measured along the horizontal center lines of the propeller planes of a semispan model representing a multiengine airplane with tractor propellers. Testing occurred at a range of Mach and Reynolds numbers. Results regarding the theoretical methods and a comparison of experimental and theoretical results are provided.
Date:
July 1956
Creator:
Lopez, Armando E. & Dickson, Jerald K.
System:
The UNT Digital Library
Measurements and Power Spectra of Runway Roughness at Airports in Countries of the North Atlantic Treaty Organization
"Measurements of runway roughness obtained by a profile-survey method are presented. A variety of runway lengths or sections and degrees of roughness were measured. The results are presented as elevation profiles of the runways surveyed and in the form of power spectra" (p. 1).
Date:
July 1958
Creator:
Thompson, Wilbur E.
System:
The UNT Digital Library
Correction of the Lifting-Line Theory for the Effect of the Chord
"It is shown that a simple correction for the chord of a finite wing can be deduced from the three-dimensional potential flow around an elliptic plate. When this flow is compared with the flow around a section of an endless plate, it is found that the edge velocity is reduced by the factor 1/E, where E is the ratio of the semiperimeter to the span. Applying this correction to the circulation brings the theoretical lift into closer agreement with experiments" (p. 1).
Date:
July 1941
Creator:
Jones, Robert T.
System:
The UNT Digital Library
Wind-tunnel investigation of effects of spoiler location, spoiler size, and fuselage nose shape on directional characteristics of a model of a tandem-rotor helicopter fuselage
Report presenting a low-speed investigation made in the stability tunnel to study the effect of spoiler location, spoiler size, and fuselage nose shape on the directional stability characteristics of a model of a tandem-rotor helicopter fuselage. The model was found to be directionally unstable at certain positive angles of attack.
Date:
July 1958
Creator:
Williams, James L.
System:
The UNT Digital Library
On the Drag and Shedding Frequency of Two-Dimensional Bluff Bodies
Note presenting a semiempirical study of the bluff-body problem. Some experiments with interference elements in the wake close behind a cylinder demonstrate the need for considering that region in any complete theory.
Date:
July 1954
Creator:
Roshko, Anatol
System:
The UNT Digital Library
Full-scale wind-tunnel tests of a 35 degree sweptback-wing airplane with blowing from the shroud ahead of the trailing-edge flaps
Report presenting a wind-tunnel investigation at full scale to determine the effect of flap location on the jet-flow momentum coefficient required to control the flap boundary layer when blowing from the wind shroud on the YF-86D airplane. The data presented show the change in lift coefficient with changes in momentum coefficient for various flap deflections, flap positions, and nozzle heights.
Date:
July 1958
Creator:
Tolhurst, William H., Jr.
System:
The UNT Digital Library
A New Hodograph for Free-Streamline Theory
Note presenting a modification introduced to allow arbitrary separation velocity and base pressure so that values more in conformity with experiment may be chosen. The solution depends on a single base-pressure parameter.
Date:
July 1954
Creator:
Roshko, Anatol
System:
The UNT Digital Library
Pressure distributions at transonic speeds for slender bodies having various axial locations of maximum diameter
Report presenting the measured static-pressure distributions at the model surfaces and in surrounding flow field for a variety of bodies of revolution with locations of maximum cross-sectional areas at 0.3, 0.4, 0.5, 0.6, and 0.7 of the body length. Data were obtained with various bodies of fineness ratio 12 at zero angle of attack.
Date:
July 1958
Creator:
McDevitt, John B. & Taylor, Robert A.
System:
The UNT Digital Library
Effects of fabrication-type roughness on turbulent skin friction at supersonic speeds
Report presenting an investigation of the effects of fabrication-type surface roughness on turbulent skin-friction drag at supersonic speeds. It was found that fabrication of the thin-skin constructions could be done sufficiently well in practice so as to cause no increase in drag over the smooth body; however, the juncture-type roughnesses produced significant increases in drag as compared with the smooth body. Results indicated that increasing the unit Reynolds number has a detrimental effect and increased the Mach number has a powerful alleviating effect on drag due to surface roughness.
Date:
July 1958
Creator:
Czarnecki, K. R.; Sevier, John R., Jr. & Carmel, Melvin M.
System:
The UNT Digital Library
Theoretical investigation of longitudinal response characteristics of a swept-wing fighter airplane having a normal acceleration control system and a comparison with other types of systems
Report presenting an investigation of the longitudinal response characteristics of a swept-wing fighter airplane using normal-acceleration control system. Results regarding the frequency and transient responses, acceleration systems, pitching-velocity command system, and the pitch-attitude system are provided.
Date:
July 1954
Creator:
Stokes, Fred H. & Mathews, Charles W.
System:
The UNT Digital Library
Heat, Mass, and Momentum Transfer for Flow Over a Flat Plate With Blowing or Suction
Note presenting testing of a woven fiberglass-nichrome wire heater cloth attached directly to the back side of the porous test wall in order to insure exact and known temperature profiles for the injected air. Suction was found to decrease the boundary-layer thickness, increase the magnitude of the friction and heat transfer coefficients, and delay the transition from laminar to turbulent flow.
Date:
July 1954
Creator:
Mickley, H. S.; Ross, R. C.; Squyers, A. L. & Stewart, W. E.
System:
The UNT Digital Library
Additional Static and Fatigue Tests of High-Strength Aluminum-Alloy Bolted Joints
From Introduction: "Early in 1951 the National Advisory Committee for Aeronautics published, as Technical Note 2276 (ref. 1), a report by the Aluminum Research Laboratories of the Aluminum Company of America on the results of static and fatigue tests of high-strength aluminum alloy monobloc specimens and bolted joints. In view of special interest shown by several aircraft companies, certain expansions of the test program were undertaken by the Aluminum Research Laboratories and are reported herein."
Date:
July 1954
Creator:
Hartmann, E. C.; Holt, Marshall & Eaton, I. D.
System:
The UNT Digital Library
Some Investigations of the General Instability of Stiffened Metal Cylinders 2: Preliminary Tests of Wire-Braced Specimens and Theoretical Studies
"This is the second of a series of reports covering an investigation of the general instability problem by the California Institute of Technology. The first five reports of this series cover investigations of the general instability problem under the loading conditions of pure bending and were prepared under the sponsorship of the Civil Aeronautics Administration. The succeeding reports of this series cover the work done on other loading conditions under the sponsorship of the National Advisory Committee for Aeronautics" (p. 1).
Date:
July 1943
Creator:
unknown
System:
The UNT Digital Library
Considerations on a large hydraulic jet catapult
Report presenting a survey of various types of catapults in connection with the problem of accelerating a large car along a track to a speed of 150 miles per hour. A hydraulic jet catapult was found to be the best suited and various design problems of that type are treated. The expected propulsive efficiency of the catapult is given and the effect of a side wind on the jet trajectory is calculated.
Date:
July 1954
Creator:
Joyner, Upshur T. & Horne, Walter B.
System:
The UNT Digital Library
An Investigation of the Creep Lifetime of 75S-T6 Aluminum-Alloy Columns
Report presenting the results of short-time elevated-temperature creep tests of 75S-T6 aluminum-alloy columns and evaluated with the objective of obtaining procedures for predicting column lifetime. Distortions resulting from creep in objects such as supersonic aircraft and missiles can cause the aerodynamic characteristics to change.
Date:
July 1954
Creator:
Mathauser, Eldon E. & Brooks, William A., Jr.
System:
The UNT Digital Library
Flight investigation of the acceptability of a small side-located controller used with an irreversible hydraulic control system
Report presenting a flight investigation to determine the acceptability of a small side-located controller which is used as the primary airplane controller in an irreversible hydraulic-power control system. Pilot opinion was obtained concerning the acceptability of the controller while performing lateral and longitudinal maneuvers in a jet-trainer airplane at cruising-flight conditions. Results indicated that the location of the controller is consistent with pilot comfort and the airplane is flyable with the side-located controller.
Date:
July 1958
Creator:
Kuehnel, Helmut A. & Sommer, Robert W.
System:
The UNT Digital Library
Effect of hydrocarbon structure on reaction processes leading to spontaneous ignition
Report presenting an investigation of 2,2,5-trimethylhexane, 2,2-dimethylbutane, and 3-heptane in regards to their susceptibility to vapor-phase oxidation and their oxidation products.
Date:
July 1955
Creator:
Swarts, Donald E. & Frank, Charles E.
System:
The UNT Digital Library
Propeller-performance charts for transport airplanes
The preliminary selection of a propeller on the basis of cruising and take-off performance for application to transport airplanes at flight Mach numbers up to 0.8 can be accomplished by the use of charts and methods presented. The charts are of sufficient scope to permit a fairly rapid evaluation of the propeller performance for engine power ratings of 1,000 to 10,000 horsepower. The method is presented primarily in the interest of propeller-noise abatement.
Date:
July 1953
Creator:
Gilman, Jean, Jr.
System:
The UNT Digital Library