National Advisory Committee for Aeronautics (NACA) - 2,223 Matching Results

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Aerodynamic Characteristics of Damping Screens

Description: From Summary: "The experimental investigation of damping screens described herein was undertaken primarily to test theories of the effects of damping screens and to obtain information on the performance of screens in oblique flow. The characteristics investigated include the damping of longitudinal and lateral components of turbulence, the effect of screens on scale, the conditions for the production of turbulence and eddies by screens, and the damping of spatial variations of mean speed."
Date: January 1950
Creator: Schubauer, G. B.; Spangenberg, W. G. & Klebanoff, P. S.
Partner: UNT Libraries Government Documents Department
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Application of the Laplace Transformation to the Solution of the Lateral and Longitudinal Stability Equations

Description: Note presenting the application of the Laplace transformation to the solution of the lateral and longitudinal stability equations. The expressions for the time history of the motion in response to a sinusoidal control motion are derived for the general case in which all initial measurements are assumed different from zero.
Date: January 1950
Creator: Mokrzycki, G. A.
Partner: UNT Libraries Government Documents Department
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The design, operation, and uses of the water channel as an instrument for the investigation of compressible-flow phenomena

Description: Report presenting the results of several years of experience of operation of a small water channel, which has shown that the hydraulic analogy can be used successfully to demonstrate many two-dimensional compressible-flow phenomena.
Date: January 1950
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department
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Effect of horizontal tail on low-speed static lateral stability characteristics of a model having 45 degree sweptback wing and tail surfaces

Description: Report presenting an investigation in the stability tunnel to determine the effects of changes in horizontal-tail size and location on the static lateral stability characteristics of a complete model with wing and tail surfaces having the quarter-chord line swept back 45 degrees. Available procedures for predicting the effect of the horizontal tail on directional stability were found to be unreliable when applied to swept-tail configurations.
Date: January 1950
Creator: Brewer, Jack D. & Lichtenstein, Jacob H.
Partner: UNT Libraries Government Documents Department
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Floating characteristics of rudders and elevators in spinning attitudes as determined from hinge-moment-coefficient data with application to personal-owner-type airplanes

Description: Report presenting a study of the available rudder and elevator hinge-moment-coefficient data in order to determine the floating characteristics of various types of rudders and elevators in spinning attitudes. Results regarding the rudder floating characteristics, elevator floating characteristics, and a comparison of several types of rudders and elevators are provided.
Date: January 1950
Creator: Bihrle, William, Jr.
Partner: UNT Libraries Government Documents Department
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Investigation of a NACA high-speed strain-gage torquemeter

Description: Report presenting an investigation of a strain-gage torquemeter employing a circuit to minimize effects of contact resistance, which was evaluated under static and dynamic conditions. Effects of temperature, axial stress, slip-ring contact resistance, and speed on the operation of the torquemeter were investigated. Results regarding the torsion-shaft static calibration, axial-stress effects, and dynamic operation are provided.
Date: January 1950
Creator: Rebeske, John J., Jr.
Partner: UNT Libraries Government Documents Department
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Linearized Supersonic Theory of Conical Wings

Description: Report presenting the theory of conical flow and its application to conical aircraft wings. Following an explanation of the theory, several types of wings are analyzed and compared with each other.
Date: January 1950
Creator: Lagerstrom, P. A.
Partner: UNT Libraries Government Documents Department
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The load distribution due to sideslip on triangular, trapezoidal, and related plan forms in supersonic flow

Description: "Expressions are presented for the load distribution on a representative group of plan forms in sideslip at supersonic speeds. These expressions were obtained by the application of lifting-surface theories based on the linearized equation for compressible flow. Sketches of the load distributions are included" (p. 1).
Date: January 1950
Creator: Jones, Arthur L. & Alksne, Alberta
Partner: UNT Libraries Government Documents Department
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Propeller Flight Investigation to Determine the Effects of Blade Loading

Description: Note presenting a flight investigation of a three-blade propeller in climb and at high speed to determine the effects of blade power loading. Increasing the blade power coefficient from 0.06 to 0.09 was found to increase the efficiency approximately 8 percent at an airplane Mach number of 0.7 and a propeller-tip Mach number of 1.13. In climb, an increase in power loading over the range of blade power coefficients investigated was shown to reduce efficiency, as a consequence of increased inducedā€¦ more
Date: January 1950
Creator: Hammack, Jerome B. & Vogeley, A. W.
Partner: UNT Libraries Government Documents Department
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Spanwise loading for wings and control surfaces of low aspect ratio

Description: Report presenting a theory based on the principle of downwash and boundary conditions, which will predict the spanwise loading due to arbitrary spanwise angle-of-attack distribution, including uniform angle of attack, that induced by rolling, spanwise variation of twist or camber, and that due to deflection of arbitrary control surfaces of low aspect ratio. For plan forms with unswept trailing edges that the spanwise loading distribution, only the slope of the region at the wing trailing edge hā€¦ more
Date: January 1950
Creator: DeYoung, John
Partner: UNT Libraries Government Documents Department
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A Theoretical Analysis of Elastic Vibrations of Fixed-Ended and Hinged Helicopter Blades in Hovering and Vertical Flight

Description: Note presenting a theoretical analysis of the frequency and damping characteristics of the free modes of vibrations of balanced fixed-ended and hinged elastic helicopter rotor blades in hovering and vertical flight. Torsional vibrations, bending vibrations in flapping and in lagging, and coupling between the flapping and lagging motions are considered.
Date: January 1950
Creator: Morduchow, Morris
Partner: UNT Libraries Government Documents Department
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Theoretical calculations of the supersonic pressure distribution and wave drag for a limited family of tapered sweptback wings with symmetrical parabolic-arc sections at zero lift

Description: Report presenting the study of the supersonic pressure distribution and wave drag of sweptback wings at zero lift, which has been extended by means of linearized theory to include the combined effects of plan-form taper and curvature of profile. Calculations have been made for a specific wing with a supersonic leading edge, which are applicable to a limited family of plan forms.
Date: January 1950
Creator: Kainer, Julian H.
Partner: UNT Libraries Government Documents Department
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A Theoretical Investigation of the Effect on the Lateral Oscillations of an Airplane of an Automatic Control Sensitive to Yawing Accelerations

Description: Report presenting an investigation to determine the effect on the lateral oscillations of an airplane of an automatic control sensitive to yawing accelerations. Results indicated that a control of that type can successfully damp the lateral oscillations through a reasonable range of time lag.
Date: January 1950
Creator: Beckhardt, Arnold R.
Partner: UNT Libraries Government Documents Department
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Charts of Airplane Acceleration Ratio for Gusts of Arbitrary Shape

Description: "The equation of vertical motion for an airplane in gusty air is simplified in order that its solution is a function of only two parameters, namely, the mass parameter of the airplane and the shape of the gust the airplane is penetrating. The solutions of the equation are presented in the form of charts that can be used for estimating rapidly and easily the acceleration ratios encountered by airplanes with different mass parameters penetrating a sharp-edge gust, a gust of arbitrary shape, or a ā€¦ more
Date: February 1950
Creator: Mazelsky, Bernard
Partner: UNT Libraries Government Documents Department
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Comparative Foaming Characteristics of Aeronautical Lubricating Oils

Description: Note presenting comparative data on the volume of foam and stability of foams of aeronautical lubricating oils produced at 100 degrees Celsius by the air-bubbling method. All of the data were obtained with the same foam meter, by a standard technique, and at various rates of air flow. Results regarding the reproducibility of foam tests and treatment of data are provided.
Date: February 1950
Creator: Woods, W. W. & Robinson, J. V.
Partner: UNT Libraries Government Documents Department
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Compressive Properties of Titanium Sheet at Elevated Temperatures

Description: "Results are presented of compressive stress-strain tests of titanium sheet at temperatures from room temperature up to 800 degrees Fahrenheit, exposure times of 1/2 to 2 hours, and strain rates of 0.002 to 0.006 per minute. The results show that titanium has favorable compressive properties, comparable to those in tension, up through 800 degrees Fahrenheit. Marked anisotropy in compression was also noted" (p. 1).
Date: February 1950
Creator: Barrett, Paul F.
Partner: UNT Libraries Government Documents Department
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Determination of the Rate of Roll of Pilotless Aircraft Research Models by Means of Polarized Radio Waves

Description: Note presenting a method for determining the rate of roll of free-flight aerodynamic models by means of polarized radio waves. The discussion shows that through the use of the technique, the direction of roll, as well as zero roll, is uniquely determined. Analysis of the data obtained and data accuracy are discussed and examples are given to show how the record-reduction method affects the accuracy of the data.
Date: February 1950
Creator: Harris, Orville R.
Partner: UNT Libraries Government Documents Department
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Effect of tunnel configuration and testing technique on cascade performance

Description: Report presenting an investigation to determine the influence of aspect ratio, boundary-layer control by means of slots and porous surfaces, Reynolds number, and tunnel end-wall condition on the performance of airfoils in cascade. A representative compressor-blade section of three aspect ratios has been tested at low speeds in cascades with solid and porous side walls.
Date: February 1950
Creator: Erwin, John R. & Emery, James C.
Partner: UNT Libraries Government Documents Department
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Effect of Valve Overlap and Compression Ratio on Variation of Measured Performance With Exhaust Pressure of Aircraft Cylinder and on Computed Performance of Compound Power Plant

Description: Note presenting an investigation conducted on an aircraft liquid-cooled single-cylinder test engine equipped with direct fuel injection to determine the effect of valve overlap and compression ratio on variation of engine power and specific fuel consumption with exhaust pressure. Results regarding the experimental engine data and compound-power-plant performance are provided.
Date: February 1950
Creator: Eian, Carroll S.
Partner: UNT Libraries Government Documents Department
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Experimental analysis of a pressure-sensitive system for sensing gas temperature

Description: Report presenting various theoretical and practical aspects of a pressure-sensitive system for the measurement of gas temperatures in gas-turbine-engine combustion chambers. An experimental setup was used under controlled conditions of temperature, weight flow, and wall temperature.
Date: February 1950
Creator: Cesaro, Richard S.; Koenig, Robert J. & Pack, George J.
Partner: UNT Libraries Government Documents Department
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An experimental investigation of the NACA 631-012 airfoil section with leading-edge and midchord suction slots

Description: Report presenting an investigation of using two suction slots in order to determine the effectiveness of a nose slot at higher values of lift. The suction through the midchord slot in conjunction with the nose slot resulted in substantial gains in the maximum lift over that obtainable with nose suction alone. Results regarding the lift, drag, and moment characteristics, pressure distribution, boundary-layer measurements, and plenum-chamber pressures are provided.
Date: February 1950
Creator: McCullough, George B. & Gault, Donald E.
Partner: UNT Libraries Government Documents Department
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First-Order Theory for Unsteady Motion of Thin Wings at Supersonic Speeds

Description: Report presenting an approximate method for determining the pressure distribution due to unsteady motion for thin wings of fairly general plan form. The method is valid for arbitrary motions when the second derivative of the perturbation velocities with respect to time is not large.
Date: February 1950
Creator: Moskowitz, Barry & Moeckel, W. E.
Partner: UNT Libraries Government Documents Department
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Foaming of Mixtures of Pure Hydrocarbons

Description: Note presenting an investigation of nine hydrocarbons mixed in pairs, sealed in glass tubes, and foamed by shaking in order to examine the foaming properties of the hydrocarbons. Results for benzene, toluene, xylene, cumene, butyl benzene, isopentane, octene, octane, and decane are provided.
Date: February 1950
Creator: Robinson, J. V. & Woods, W. W.
Partner: UNT Libraries Government Documents Department
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Friction and wear of hot-pressed bearing materials containing molybdenum disulfide

Description: Report presenting an investigation to determine the feasibility of bearing lubrication by a process involving the transfer of molybdenum disulfide from within the structure of a composite bearing material to the interface between the contacting surfaces. The experiments were performed with a kinetic-friction apparatus employing a rotating steel disk and a bearing-specimen assembly suspended and restrained by metal springs.
Date: February 1950
Creator: Johnson, Robert L.; Swikert, Max A. & Bisson, Edmond E.
Partner: UNT Libraries Government Documents Department
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