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Wind-tunnel investigation of an external-flow jet-augmented slotted flap suitable for application to airplanes with pod-mounted jet engines
Report presenting a wind-tunnel investigation to determine the characteristics of an external-flow jet-augmented slotted flap which appears suitable for applications to pod-mounted jet engines. The investigation included tests of an unswept wing and of a model of a swept-wing jet transport or bomber. Results regarding the unswept wings, swept wings, longitudinal stability and trim, and estimated take-off and landing performance are provided.
Date:
December 1956
Creator:
Campbell, John P. & Johnson, Joseph L., Jr.
System:
The UNT Digital Library
Span load distributions resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration for tapered sweptback wings with streamwise tips: Subsonic leading edges and supersonic trailing edges
Report presenting the theoretical spanwise distributions of circulation resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration calculated for a series of thin, sweptback, tapered wings with streamwise tips.
Date:
December 1952
Creator:
Hannah, Margery E. & Margolis, Kenneth
System:
The UNT Digital Library
Theoretical study of the transonic lift of a double-wedge profile with detached bow wave
Report presenting a theoretical study of the aerodynamic characteristics at small angle of attack of a thin, double-wedge profile in the range of supersonic flight speed in which the bow wave is detached. The calculations provide, for extremely small angles of attack, the following information as a function of the transonic similarity parameter: chordwise lift distribution, lift-curve slope, and position of center of lift.
Date:
December 1952
Creator:
Vincenti, Walter G. & Wagoner, Cleo B.
System:
The UNT Digital Library
Ignition delays and fluid properties of several fuels and nitric acid oxidants in temperature range from 70 to -105 degrees Fahrenheit
Report presenting ignition-delay characteristics of approximately 90 fuel-oxidant combinations determined in a modified open-cup apparatus at -40 degrees Fahrenheit. Freezing temperatures of acids were determined as well as viscosities of several fuels at moderate and low temperatures. Results regarding fluid properties of fuels and oxidants at low temperatures, an ignition study of the acid oxidants, an ignition study of fuels, and practical aspects of working with the oxidants and fuels are provided.
Date:
December 1956
Creator:
Miller, Riley O.
System:
The UNT Digital Library
Investigation of Transient Pool Boiling Due to Sudden Large Power Surge
Note presenting an investigation of the transfer of heat from a metallic ribbon to water, under transient conditions, for initial water temperatures from 76 to 203 degrees Fahrenheit and average heat-generation rates per square foot of square area of 3, 10, and 20x10(exp 5) Btu per hour per square foot. Results regarding the nucleate boiling region, film boiling region, and critical heat flux are provided.
Date:
December 1956
Creator:
Cole, Robert
System:
The UNT Digital Library
Use of a Hot-Wire Anemometer in Shock-Tube Investigations
Note presenting the use of the hot-wire anemometer as an instrument for experimental investigations of the transient flow phenomena in a shock tube. The response of a hot-wire to a transient step-function type of change in flow conditions is studied and a criterion for predicting the right compensation is theorized and experimentally verified.
Date:
December 1954
Creator:
Dosanjh, Darshan Singh
System:
The UNT Digital Library
Investigation of the effects of propeller diameter on the ability of a flapped wing, with and without boundary-layer control, to deflect a propeller slipstream downward for vertical take-off
Report presenting an investigation to study the effects of propeller diameter on the ability of a flapped wing, with and without boundary-layer control, to deflect propeller slipstreams downward for vertical take-off. The results indicated that without boundary-layer control, an increase in the ratio of flap chord to propeller diameter increases the turning angle but decreases the ratio of resultant force to thrust.
Date:
December 1957
Creator:
Spreemann, Kenneth P.
System:
The UNT Digital Library
Experimental investigation of two-dimensional tunnel-wall interference at high subsonic speeds
Report presenting a determination of the tunnel-wall interference for a two-dimensional-flow, rectangular, closed-throat wind tunnel over a range of Mach numbers. Aerodynamic data obtained showed that the influence of the walls becomes progressively greater with increasing Mach number and increasing chord-height ratio.
Date:
December 1953
Creator:
Knechtel, Earl D.
System:
The UNT Digital Library
Determination of the Flying Qualities of the Douglas DC-3 Airplane
Report presenting an evaluation of the flying qualities of the Douglas DC-3 airplane to determine its longitudinal and lateral stability and control characteristics and its stalling behavior.
Date:
December 1953
Creator:
Assadourian, Arthur & Harper, John A.
System:
The UNT Digital Library
On the Analysis of Linear and Nonlinear Dynamical Systems From Transient-Response Data
Note presenting a general theory of the so-called equations of motion methods for the analysis of linear dynamical systems. When viewed from this general vantage point, all of the linear methods can be extended in a straightforward manner to apply to the analysis of nonlinear systems.
Date:
December 1954
Creator:
Shinbrot, Marvin
System:
The UNT Digital Library
Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber
From Introduction: "The analysis of flight data in the present report is, to a large extent, based on analyses and information contained in references 1 and 2 for wing deflections, reference 3 for horizontal-tail parameters, reference 4 for airplane lift-curve slopes and angles of zero lift, and reference 5 for wing centers of pressure."
Date:
December 1957
Creator:
Aiken, William S., Jr.
System:
The UNT Digital Library
Three-Degree-of Freedom Evaluation of the Longitudinal Transfer Functions of a Supersonic Canard Missile Configuration Including Changes in Forward Speed
Note presenting a reevaluation of existing flight data obtained for a supersonic canard missile configuration of the boost-glide type to determine derivatives not previously evaluated. The derivatives are utilized to determine some typical airframe frequency responses based on the three-degree-of-freedom longitudinal equations of motion. Results regarding derivatives, frequency responses, and three-degree-of-freedom approach to future automatic-control studies are provided.
Date:
December 1957
Creator:
Seaberg, Ernest C.
System:
The UNT Digital Library
An experimental and theoretical study of the effect of fuel on pitching-translation flutter
Report presenting analytical flutter studies made for 2 two-dimensional fuel-loading wing models, as well as comparisons of experimental results for bending-to-torsion frequency ratios near 1.
Date:
December 1957
Creator:
Sewall, John L.
System:
The UNT Digital Library
A reexamination of the use of simple concepts for predicting the shape and location of detached shock waves
A reexamination has been made of the use of simple concepts for predicting the shape and location of detached shock waves. The results show that simple concepts and modifications of existing methods can yield good predictions for many nose shapes and for a wide range of Mach numbers.
Date:
December 1957
Creator:
Love, Eugene S.
System:
The UNT Digital Library
Effect of type of porous surface and suction velocity distribution on the characteristics of a 10.5-percent-thick airfoil with area suction
Report presenting an investigation at low-speed of the two-dimensional characteristics of a 10.51-percent-thick symmetrical airfoil with area suction for boundary-layer control near the leading edge. The lift and suction-flow characteristics were determined with different porous surfaces for various suction velocity distributions obtained by varying the permeability arrangement. Results regarding the plain airfoil, airfoil with various chordwise extents of area suction, effect of external surface and permeability arrangement, and effect of free-stream velocity are provided .
Date:
December 1953
Creator:
Dannenberg, Robert E. & Weiberg, James A.
System:
The UNT Digital Library
A flight investigation of laminar and turbulent boundary layers passing through shock waves at full-scale Reynolds numbers
Report presenting an investigation in flight at free-stream Mach numbers up to 0.76 to determine the behavior of laminar and turbulent boundary layers passing through shock waves. Boundary-layer and pressure-distribution measurements were made on a short-span airfoil built around a wing of a fighter airplane. Results regarding laminar flow ahead of the shock wave, turbulent flow ahead of the shock wave, comparison at full scale of laminar and turbulent boundary layers, and effect of Reynolds numbers on boundary-layer profiles with shock waves are provided.
Date:
December 1953
Creator:
Harrin, Eziaslav N.
System:
The UNT Digital Library
Investigation at supersonic speeds of the wave drag of seven boattail bodies of revolution designed for minimum wave drag
Report presenting an investigation in the 9-inch supersonic tunnel to determine the effects of varying Reynolds number at each of three Mach numbers on the wave drag of seven boattail bodies of revolution designed for minimum wave drag. Results indicated that there was little variation in the pressure distribution with Reynolds number. Results regarding pressure distributions and wave drag are provided.
Date:
December 1953
Creator:
Bromm, August F., Jr. & Goodwin, Julia M.
System:
The UNT Digital Library
Effects of leading-edge blunting on the local heat transfer and pressure distributions over flat plates in supersonic flow
Report presenting an investigation of the effect of leading-edge thickness on the flow over flat plates with square and cylindrical blunting at Mach number 4 and free-stream Reynolds numbers per inch of 2380 and 6600. For test conditions, the bow shock wave was detached and leading-edge shape had no effect on surface pressures aft of two leading-edge thicknesses. Results regarding surface pressure, flow-field surveys, heat transfer, boundary-layer thickness, surface pressure distribution, local Mach number, local Reynolds number, and heat transfer are provided.
Date:
December 1957
Creator:
Creager, Marcus O.
System:
The UNT Digital Library
Use of electric analog for calculation of temperature distribution of cooled turbine blades
Report presenting an investigation to develop simple, inexpensive electric analogs for determining temperatures of cooled turbine blades. Analogs were made for a 13-fin shell-supported air-cooled blade, a strut-supported air-cooled blade, and a liquid-cooled blade.
Date:
December 1953
Creator:
Ellerbrock, Herman H., Jr.; Schum, Eugene F. & Nachtigall, Alfred J.
System:
The UNT Digital Library
Investigation of Sandwich Construction Under Lateral and Axial Loads
Note presenting testing under combined axial load and lateral pressure on 12 bonded sandwich panels with simply supported loaded edges and free unloaded edges. The maximum load and mode of failure were observed for all the panels. Lateral deflections and axial strains were also measured.
Date:
December 1953
Creator:
Kroll, Wilhelmina D.; Mordfin, Leonard & Garland, William A.
System:
The UNT Digital Library
Stresses Around Rectangular Cutouts in Torsion Boxes
Note presenting a method for calculating the stresses produced by rectangular cutouts of any size in torsion boxes. The problem is divided into a "box problem" and a "cover problem". Three sets of tests are provided.
Date:
December 1953
Creator:
Kuhn, Paul & Peterson, James P.
System:
The UNT Digital Library
Analysis of Multicell Delta Wings on Cal-Tech Analog Computer
"The main purpose of this paper is to present the results of measurements made on the Cal-Tech computer. The diagrams present only a small portion of the data which were obtained from the computer and which are given in complete form in the tables" (p. 1-2).
Date:
December 1953
Creator:
MacNeal, Richard H. & Benscoter, Stanley U.
System:
The UNT Digital Library
A Theoretical Investigation of the Short-Period Dynamic Longitudinal Stability of Airplane Configurations Having Elastic Wings of 0 Degree to 60 Degrees Sweepback
Note presenting a theoretical investigation made to determine the effects of an elastic wing on the dynamic longitudinal stability of thin-wing airplane configuration. In order to investigate the effects of various important parameters, the configurations were assumed to vary in wing sweep angle from 0 to 60 degrees, in center-of-gravity location from 25 percent mean aerodynamic chord to 45 percent mean aerodynamic chord, and in ratio of wing mass to airplane mass from 0.15 to 0.50.
Date:
December 1954
Creator:
McLaughlin, Milton D.
System:
The UNT Digital Library
An investigation of a wing-propeller configuration employing large-chord plain flaps and large-diameter propellers for low-speed flight and vertical take-off
Report presenting an investigation of the effectiveness of a wing equipped with large-chord plain flaps and auxiliary vanes in rotating the thrust vector of two large-diameter propellers through the large angles required for vertical take off and low-speed flight. The semispan model was equipped with a 60-percent-chord flap, a 30-percent-chord flap, and two large-diameter overlapping propellers. Results regarding static thrust conditions, tests with forward speed, and application of results are provided.
Date:
December 1954
Creator:
Kuhn, Richard E. & Draper, John W.
System:
The UNT Digital Library