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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Serial/Series Title: NACA Technical Reports
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics at high speeds of related full-scale propellers having different blade-section cambers

Aerodynamic characteristics at high speeds of related full-scale propellers having different blade-section cambers

Date: January 1, 1957
Creator: Maynard, Julian D & Salters, Leland B , Jr
Description: Wind-tunnel tests of a full-scale two-blade NACA 10-(10)(08)-03 (high camber) propeller have been made for a range of blade angles from 20 degrees to 55 degrees at airspeeds up to 500 miles per hour. The results of these tests have been compared with results from previous tests of the NACA 10-(3) (08)-03 (low camber) and NACA 10-(5)(08)-03 (medium camber) propellers to evaluate the effects of blade-section camber on propeller aerodynamic characteristics.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the effects of aeroelasticity on static longitudinal stability and control of a swept-wing airplane

An analysis of the effects of aeroelasticity on static longitudinal stability and control of a swept-wing airplane

Date: January 1, 1957
Creator: Skoog, Richard B
Description: A theoretical analysis has been made of the effects of aeroelasticity on the static longitudinal stability and elevator angle required for balance of an airplane. The analysis is based on the familiar stability equation expressing the contribution of wing and tail to longitudinal stability. Effects of wing, tail, and fuselage flexibility are considered. Calculated effects are shown for a swept-wing bomber of relatively high flexibility.
Contributing Partner: UNT Libraries Government Documents Department
Attenuation in a shock tube due to unsteady-boundary-layer action

Attenuation in a shock tube due to unsteady-boundary-layer action

Date: January 1, 1957
Creator: Mirels, Harold
Description: A method is presented for obtaining the attenuation of a shock wave in a shock tube due to the unsteady boundary layer along the shock-tube walls. It is assumed that the boundary layer is thin relative to the tube diameter and induces one-dimensional longitudinal pressure waves whose strength is proportional to the vertical velocity at the edge of the boundary layer. The contributions of the various regions in a shock tube to shock attenuation are indicated. The method is shown to be in reasonably good agreement with existing experimental data.
Contributing Partner: UNT Libraries Government Documents Department
Average properties of compressible laminar boundary layer on flat plate with unsteady flight velocity

Average properties of compressible laminar boundary layer on flat plate with unsteady flight velocity

Date: January 1, 1957
Creator: Moore, Franklin K & Ostrach, Simon
Description: The time-average characteristics of boundary layers over a flat plate in nearly quasi-steady flow are determined. The plate may be either insulated or isothermal. The time averages are found without specifying the plate velocity explicitly except that it is positive and has an average value.
Contributing Partner: UNT Libraries Government Documents Department
Basic considerations in the combustion of hydrocarbon fuels with air

Basic considerations in the combustion of hydrocarbon fuels with air

Date: January 1, 1957
Creator: Barnett, Henry C & Hibbard, Robert R
Description: Basic combustion research is collected, collated, and interpreted as it applies to flight propulsion. The following fundamental processes are treated in separate chapters: atomization and evaporation of liquid fuels, flow and mixing processes in combustion chambers, ignition and flammability of hydrocarbon fuels, laminar flame propagation, turbulent flames, flame stabilization, diffusion flames, oscillations in combustors, and smoke and coke formation in the combustion of hydrocarbon-air mixtures. Theoretical background, basic experimental data, and practical significance to flight propulsion are presented.
Contributing Partner: UNT Libraries Government Documents Department
Bodies of revolution having minimum drag at high supersonic airspeeds

Bodies of revolution having minimum drag at high supersonic airspeeds

Date: January 1, 1957
Creator: Eggers, A J , Jr; Resnikoff, Meyer M & Dennis, David H
Description: Approximate shapes of nonlifting bodies having minimum pressure foredrag at high supersonic airspeeds are calculated. With the aid of Newton's law of resistance, the investigation is carried out for various combinations of the conditions of given body length, base diameter, surface area, and volume. In general, it is found that when body length is fixed, the body has a blunt nose; whereas, when the length is not fixed, the body has a sharp nose. The additional effect of curvature of the flow over the surface is investigated to determine its influence on the shapes for minimum drag. The effect is to increase the bluntness of the shapes in the region of the nose and the curvature in the region downstream of the nose. These shape modifications have, according to calculation, only a slight tendency to reduce drag. Several bodies of revolution of fineness ratios 3 and 5, including the calculated shapes of minimum drag for given length and base diameter and for given base diameter and surface area, were tested at Mach numbers from 2.73 to 6.28. A comparison of theoretical and experimental foredrag coefficients indicates that the calculated minimum-drag bodies are reasonable approximations to the correct shape.
Contributing Partner: UNT Libraries Government Documents Department
Cloud-droplet ingestion in engine inlets with inlet velocity ratios of 1.0 and 0.7

Cloud-droplet ingestion in engine inlets with inlet velocity ratios of 1.0 and 0.7

Date: January 1, 1957
Creator: Brun, Rinaldo J
Description: The paths of cloud droplets into two engine inlets have been calculated for a wide range of meteorological and flight conditions. The amount of water in droplet form ingested by the inlets and the amount and distribution of water impinging on the inlet walls are obtained from these droplet-trajectory calculations. In both types of inlet, a prolate ellipsoid of revolution represents either part or all of the forebody at the center of an annular inlet to an engine. The configurations can also represent a fuselage of an airplane with side ram-scoop inlets. The studies were made at an angle of attack of 0 degree. The principal difference between the two inlets studied is that the inlet-air velocity of one is 0.7 that of the other. The studies of the two velocity ratios lead to some important general concepts of water ingestion in inlets.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of several methods for obtaining the time response of linear systems to either a unit impulse or arbitrary input from frequency-response data

Comparison of several methods for obtaining the time response of linear systems to either a unit impulse or arbitrary input from frequency-response data

Date: January 1, 1957
Creator: Donegan, James J & Huss, Carl R
Description: Several methods of obtaining the time response of Linear systems to either a unit impulse or an arbitrary input from frequency-response data are described and compared. Comparisons indicate that all the methods give good accuracy when applied to a second-order system; the main difference is the required computing time. The methods generally classified as inverse Laplace transform methods were found to be most effective in determining the response to a unit impulse from frequency-response data of higher order systems. Some discussion and examples are given of the use of such methods as flight-data-analysis techniques in predicting loads and motions of a flexible aircraft on the basis of simple calculations when the aircraft frequency response is known.
Contributing Partner: UNT Libraries Government Documents Department
Correlation, evaluation, and extension of linearized theories for tire motion and wheel shimmy

Correlation, evaluation, and extension of linearized theories for tire motion and wheel shimmy

Date: January 1, 1957
Creator: Smiley, Robert F
Description: An evaluation is made of the existing theories of a linearized tire motion and wheel shimmy. It is demonstrated that most of the previously published theories represent varying degrees of approximation to a summary theory developed in this report which is a minor modification of the basic theory of Von Schlippe and Dietrich. In most cases where strong differences exist between the previously published theories and summary theory, the previously published theories are shown to possess certain deficiencies. A series of systematic approximations to the summary theory is developed for the treatment of problems too simple to merit the use of the complete summary theory, and procedures are discussed for applying the summary theory and its systematic approximations to the shimmy of more complex landing-gear structures than have previously been considered. Comparisons of the existing experimental data with the predictions of the summary theory and the systematic approximations provide a fair substantiation of the more detailed approximate theories.
Contributing Partner: UNT Libraries Government Documents Department
Determination of longitudinal stability and control characteristics from free-flight model tests with results at transonic speeds for three airplane configurations

Determination of longitudinal stability and control characteristics from free-flight model tests with results at transonic speeds for three airplane configurations

Date: January 1, 1957
Creator: Gillis, Clarence L & Mitchell, Jesse L
Description: A test technique and data analysis method has been developed for determining the longitudinal aerodynamic characteristics from free-flight tests of rocket-propelled models. The technique makes use of accelerometers and an angle-of-attack indicator to permit instantaneous measurements of lift, drag, and pitching moments. The data, obtained during transient oscillations resulting from control-surface disturbances, are analyzed by essentially nonlinear direct methods (such as cross plots of the variation of lift coefficient with angle of attack) and by linear indirect methods by using the equations of motion for a transient oscillation. The analysis procedure has been set forth in some detail and the feasibility of the method has been demonstrated by data measured through the transonic speed range on several airplane configurations. It was shown that the flight conditions and dynamic similitude factors for the tests described were reasonably close to typical full-scale airplane conditions.
Contributing Partner: UNT Libraries Government Documents Department
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