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Abnormal grain growth in nickel-base heat-resistant alloys
From Introduction: "The data included in this report for Nimonic 80A alloy, for instance, represent experiments carried out to help clarify a production problem of grain-size control in an alloy which has been extensively used. The general procedure of the investigation was to carry out controlled laboratory experiments on samples of bar stock to find conditions of heating and hot-working which resulted in abnormal grain growth."
Date:
December 1957
Creator:
Decker, R. F.; Rush, A. I.; Dano, A. G. & Freeman, J. W.
System:
The UNT Digital Library
Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)
Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aerodynamic characteristics of the NACA 8-H-12 airfoil section at four Reynolds numbers. The section lift, drag, and pitching-moment characteristics are presented for smooth and rough surface conditions. Generally, no unusual scale effects are present for either condition.
Date:
December 1949
Creator:
Schaefer, Raymond F. & Smith, Hamilton A.
System:
The UNT Digital Library
The Aerodynamic Design of Supersonic Propellers from Structural Considerations
From Summary: "The aerodynamic design of propellers from considerations of centrifugal force is presented. By applying a constant minimum value of thickness ratio from root to tip and allowing the distribution of required area to appear in the blade plan form, propellers with good efficiency are realized at high Mach numbers by the method of this paper."
Date:
December 1952
Creator:
Hammack, Jerome B.
System:
The UNT Digital Library
The Aerodynamic Drag of Five Models of Side Floats N.A.C.A. Models 51-E, 51-F, 51-G, 51-H, 51-J
"The drag of five models of side floats was measured in the N.A.C.A. 7- by 10-foot wind tunnel. The most promising method of reducing the drag of floats indicated by these tests is lowering the angle at which the floats are rigged. The addition of a step to a float does not always increase the drag in the flying range, floats with steps sometimes having lower drag than similar floats without steps" (p. 1).
Date:
December 1938
Creator:
House, R. O.
System:
The UNT Digital Library
Aerodynamic Effects of a Split Flap on the Spinning Characteristics of a Monoplane Model
From Summary: "The investigation described in this report was made to determine the change in aerodynamic forces and moments produced by split flaps in a steady spin. The test were made with the spinning balance in the NACA 5-foot vertical wind tunnel. A low-wing monoplane model was tested with and without the split flaps in 12 spinning attitudes chosen to cover the probable spinning range. The results obtained indicate that the use of split flaps on an airplane is unlikely, in any case, to have much beneficial effect on a spin, and it might make the spin dangerous."
Date:
December 1934
Creator:
Bamber, M. J.
System:
The UNT Digital Library
Analysis and modification of theory for impact of seaplanes on water
From Summary: "An analysis of available theory on seaplane impact and a proposed modification thereto are presented."
Date:
December 1945
Creator:
Mayo, Wilbur L.
System:
The UNT Digital Library
An analysis of an x-ray absorption method for measurement of high gas temperatures
From Introduction: "A theoretical analysis of the factors involved in the measurement of the temperature of gaseous combustion products by the X-ray absorption method is presented herein."
Date:
December 1951
Creator:
Weltmann, Ruth N. & Kuhns, Perry W.
System:
The UNT Digital Library
An analysis of flow in rotating passage of large radial-inlet centrifugal compressor at tip speed of 700 feet per second
Report presenting an analysis of the flow in the rotating passages of a 48-inch diameter radial-inlet centrifugal impeller at a tip speed of 700 feet per second in order to provide more information on the flow conditions within the impeller. Results regarding the impeller and diffuser performance, design flow characteristics, and off-design flow characteristics are provided.
Date:
December 1951
Creator:
Prian, Vasily D. & Michel, Donald J.
System:
The UNT Digital Library
Analysis of Ground Effect on the Lifting Airscrew
"A study is presented of ground effect as applied to the lifting airscrew of the type used in modern gyroplanes and helicopters. The mathematical analysis of the problem has been verified by tests made of three rotor models in the presence of a large circular "ground plane." The results of the study are presented in the form of convenient charts" (p. 1).
Date:
December 1941
Creator:
Knight, Montgomery & Hefner, Ralph A.
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
Analysis of means of improving the uncontrolled lateral motions of personal airplanes
From Summary: "The purpose of this investigation was to determine whether such airplanes could be made to fly uncontrolled for an indefinite period of time without getting into dangerous attitudes and for a reasonable period of time (one to three minutes) without deviating excessively from their original course. The results of this analysis indicated that the uncontrolled motions of a personal airplane could be made safe as regards spiral tendencies and could be greatly improved as regards maintenance of course without resort to an autopilot."
Date:
December 1949
Creator:
McKinney, Marion O., Jr.
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
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
Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-Pipe Shrouds
Investigations were made to develop a simplified method for designing exhaust-pipe shrouds to provide desired or maximum cooling of exhaust installations. Analysis of heat exchange and pressure drop of an adequate exhaust-pipe shroud system requires equations for predicting design temperatures and pressure drop on cooling air side of system. Present experiments derive such equations for usual straight annular exhaust-pipe shroud systems for both parallel flow and counter flow. Equations and methods presented are believed to be applicable under certain conditions to the design of shrouds for tail pipes of jet engines.
Date:
December 1947
Creator:
Ellerbrock, Herman H., Jr.; Wcislo, Chester R. & Dexter, Howard E.
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
Analytical determination of the natural coupled frequencies and mode shapes and the response to oscillating forcing functions of tandem helicopters
Report presenting a method for the analytical determination of the natural coupled frequencies and mode shapes of vibrations in the vertical plane of tandem helicopters. That information is then used to calculate the response of the helicopter to applied oscillation forces. Calculated response curves show how the vibrations of the cockpit vary with frequency and method of application of oscillating forces applied at the hubs.
Date:
December 1956
Creator:
Brooks, George W. & Houbolt, John C.
System:
The UNT Digital Library
An Analytical Estimation of the Effect of Transpiration Cooling on the Heat-Transfer and Skin-Friction Characteristics of a Compressible, Turbulent Boundary Layer
"An analysis based on mixing-length theory is presented which indicates that surface blowing associated with transpiration cooling systems produce large reductions in both the heat-transfer and skin-friction coefficients for a turbulent boundary layer on a flat plate. The numerical results are restricted to the case of air blowing into air. The effects of blowing are indicated to be similar for high-speed, compressible flow to those for low-speed, incompressible flow" (p. 1).
Date:
December 1954
Creator:
Rubesin, Morris W.
System:
The UNT Digital Library
An Analytical Investigation of the Gust-Alleviating Properties of a Simple Pitch Damper
From Introduction: "The present paper is to investigate analytically the alleviation that can be obtained by a relatively simple system which alters the longitudinal motions induced by the direct effect of the gust loads."
Date:
December 1957
Creator:
Crabill, Norman L.
System:
The UNT Digital Library
An analytical investigation using aerodynamic limitations of several designs of high stage pressure ratio multistage compressors
From Introduction: "As more quantitative information becomes available, more will be known of the maximum stage total-pressure ratios that can be used while maintaining acceptable efficiences and weight flows. Because quantitative knowledge is limited, the qualitative nature of limiting factors and trends are investigated herein."
Date:
December 1951
Creator:
Voit, Charles H. & Thomson, Arthur R.
System:
The UNT Digital Library
Application of the Von Kármán momentum theorem to turbulent boundary layers
Report presenting a study of the Von Kármán momentum theorum with respect to its application to turbulent boundary layers in a positive pressure gradient. The results indicate that the streamwise derivative of the turbulent longitudinal momentum may be large near the separation and therefore should be considered when the momentum theorum is used for turbulent boundary layers near separation.
Date:
December 1951
Creator:
Bidwell, Jerold M.
System:
The UNT Digital Library
Approximate Calculation of the Compressible Turbulent Boundary Layer With Heat Transfer and Arbitrary Pressure Gradient
Note presenting an approximate method for the calculation of compressible turbulent boundary layer with heat transfer and arbitrary pressure gradient. The method involves the momentum integral and moment-of-momentum equations as simplified by using Stewartson's transformation.
Date:
December 1957
Creator:
Reshotko, Eli & Tucker, Maurice
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
Approximate methods for calculating the flow about nonlifting bodies of revolution at high supersonic airspeeds
Explicit expressions are developed which yield the Mach number and pressure distributions on the surfaces of pointed nonlifting bodies of revolution operating at high supersonic airspeeds and at values of the hypersonic similarity parameter (ratio of free-stream Mach number to slenderness ratio) greater than 1. Very simple explicit expressions are obtained for these distributions in the special case of slender bodies. In the case of cones, the analytic solutions accurately define the entire flow field over a wide range of free-stream Mach numbers and apex angles.
Date:
December 1951
Creator:
Eggers, A. J., Jr. & Savin, Raymond C.
System:
The UNT Digital Library
Average Properties of Compressible Laminar Boundary Layer on Flat Plate With Unsteady Flight Velocity
Note presenting a determination of the time-average characteristics of boundary layers over a flat plate in nearly quasi-steady flow. The time averages were found without specifying the plate velocity explicitly except that it is positive and has an average value. Some remarks on the heat-transfer problem are also provided.
Date:
December 1956
Creator:
Moore, Franklin K. & Ostrach, Simon
System:
The UNT Digital Library