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Calculation of the forces and moments on a slender fuselage and vertical fin penetrating lateral gusts

Description: A theory is presented for calculating the variation with frequency of the lateral-force and yawing-moment coefficients due to sinusoidal side gusts passing over the profile of a simple fuselage-vertical-fin combination. The analysis is based on slender-body theory. The method considers the penetration effect of both fuselage and vertical tail in calculating side force and yawing moment due to side gusts, as opposed to a simple lag concept which considers the flow angle to be uniform over the configuration.
Date: October 1956
Creator: Eggleston, John M.
Partner: UNT Libraries Government Documents Department

A method of deriving frequency-response data for motion of the center of gravity from data measured on an aircraft at locations other than the center of gravity

Description: Report presenting a method for driving time-response and frequency-response data for angle of attack and normal acceleration at the center of gravity of an aircraft when the data are measured at locations on the aircraft other than the center of gravity and when the pitching velocity is not measured.
Date: October 1953
Creator: Eggleston, John M.
Partner: UNT Libraries Government Documents Department

A theory for the lateral response of airplanes to random atmospheric turbulence

Description: Report presenting a derivation of the lateral motions of an airplane flying through continuous random isotropic turbulence in terms of three different functions and sets of forces. Three airplanes of different size are used to demonstrate the method, illustrate characteristic trends, and exhibit some simplifications possible in the calculations.
Date: May 1957
Creator: Eggleston, John M.
Partner: UNT Libraries Government Documents Department

A method for the calculation of the lateral response of airplanes to random turbulence

Description: In this method, the gust velocities are represented as rolling gusts, yawing gusts, and side gusts. Random distributions of gust velocities across the span are taken into account in defining the rolling and yawing gusts. Complex stability derivatives are used to account for the random distribution of side gusts along the fuselage and vertical tail and the lag effects in gust penetration. A sample calculation procedure is presented for obtaining the response of the airplane in each degree of freedom.
Date: February 1958
Creator: Eggleston, John M. & Phillips, William H.
Partner: UNT Libraries Government Documents Department

Application of several methods for determining transfer functions and frequency response of aircraft from flight data

Description: In the process of analyzing the longitudinal frequency-response characteristics of aircraft, information on some of the methods of analysis has been obtained by the Langley Aeronautical Laboratory of the National Advisory Committee for Aeronautics. In the investigation of these methods, the practical applications and limitations were stressed. In general, the methods considered may be classed as: (1) analysis of sinusoidal response, (2) analysis of transient response as to harmonic content through determination of the Fourier integral by manual or machine methods, and (3) analysis of the transient through the use of least-squares solutions of the coefficients of an assumed equation for either the transient time response or frequency response (sometimes referred to as curve-fitting methods). (author).
Date: 1954
Creator: Eggleston, John M. & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department

Application of several methods for determining transfer functions and frequency response of aircraft from flight data

Description: Report presenting an investigation of the methods of analyzing longitudinal frequency-response characteristics of aircraft. The methods considered are analysis of sinusoidal response, analysis of transient response to harmonic content through determination of the Fourier integral, and analysis of the transient through the use of least-squares solutions of the coefficients of an assume equation for the transient time or frequency response.
Date: September 1953
Creator: Eggleston, John M. & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department

Theoretical calculation of the power spectra of the rolling and yawing moments on a wing in random turbulence

Description: Report presenting calculations of the correlation functions and power spectra of the rolling and yawing moments on an airplane wing due to the three components of continuous random turbulence. Specific numerical calculations are made for a pair of correlation functions given by simple analytic expressions which fit available experimental data.
Date: December 1956
Creator: Eggleston, John M. & Diederich, Franklin W.
Partner: UNT Libraries Government Documents Department

Theoretical calculation of the power spectra of the rolling and yawing moments on a wing in random turbulence

Description: The correlation functions and power spectra of the rolling and yawing moments on an airplane wing due to the three components of continuous random turbulence are calculated. The rolling moments to the longitudinal (horizontal) and normal (vertical) components depend on the spanwise distributions of instantaneous gust intensity, which are taken into account by using the inherent properties of symmetry of isotropic turbulence. The results consist of expressions for correlation functions or spectra of the rolling moment in terms of the point correlation functions of the two components of turbulence.
Date: September 6, 1956
Creator: Eggleston, John M. & Diederich, Franklin W.
Partner: UNT Libraries Government Documents Department

A Transonic Investigation by the Free-Fall Method of an Airplane Configuration Having 45 Degrees Sweptback Wing and Tail Surfaces

Description: Report presenting a free-fall investigation of airplanes in the transonic range using a configuration with 45 degree sweptback wing and tail surfaces. The lift, drag, and longitudinal static and dynamic stability and control characteristics were obtained at a range of operating lift coefficients and Mach numbers.
Date: June 11, 1953
Creator: Faber, Stanley & Eggleston, John M.
Partner: UNT Libraries Government Documents Department

Flight Investigation of the Longitudinal Stability and Control Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Up to 0.89

Description: Report presenting results and analysis of the longitudinal stability and control characteristics of the Douglas D-558-I airplane at a range of altitudes and Mach numbers. It was found that large and rapid changes in elevator deflection and force were required for balance at Mach numbers above 0.84 due to a sharp decrease in elevator-stabilizer effectiveness.
Date: June 25, 1951
Creator: Sadoff, Melvin; Roden, William S. & Eggleston, John M.
Partner: UNT Libraries Government Documents Department

Flight Investigation of the Aileron Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Between 0.6 and 0.89

Description: "Abrupt, rudder-fixed aileron rolls have been made with the Douglas D-558-I airplane (BuAero No. 37972) at Mach numbers between 0.6 and 0.89. Rolls were made at aileron deflections between one-eighth and one-half the maximum available deflection. The results obtained indicate that the aileron effectiveness is independent of Mach number and deflection within the range investigated" (p. 1).
Date: May 26, 1950
Creator: Thompson, Jim Rogers; Roden, William S. & Eggleston, John M.
Partner: UNT Libraries Government Documents Department