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1	The economic justification and operational requirements of high-speed runway exits Zhong, Caoyuan 04 December 2009 (has links) The objective of this thesis is to analyze the operational requirements of aircraft during the runway exiting maneuvers and the economic feasibility of high-speed runway exits. The motion of the aircraft is simulated by a computer program based on the appropriate equations of motion and steering inputs. The economic analysis of high-speed runway exits is based on a life cycle cost approach. Historical data of airline operating costs are also used in the cost estimations. The results show that high-speed runway exits are operationally feasible and economically profitable. The results are also presented graphically to show the effect of various steering commands on the vehicle turning maneuvering requirements and the effect of different economic parameters to the evaluation of high-speed exit utilizations. / Master of Science LD5655.V855 1992.Z466 Airplanes -- Takeoff Runways (Aeronautics) -- Costs
2	Numerical simulation of feedback control of aerodynamic configurations in steady and unsteady ground effects Nuhalt, Abdullah O. January 1988 (has links) A general numerical simulation of closely coupled lifting surfaces in steady and unsteady ground effects was developed. This model was coupled with the equations of motion to simulate aerodynamic-dynamic interaction. The resulting model was then coupled with a feedback-control law to form a general nonlinear unsteady numerical simulation of control of an aircraft in and out of ground effect. The aerodynamic model is based on the general unsteady vortex-lattice method and the method of images. It is not restricted by planform, angle of attack, sink rate, dihedral angle, twist, camber, etc. as long as stall or vortex bursting does not occur. In addition, it has the versatility to model steady and unsteady aerodynamic interference. The present model can be used to simulate any prescribed flare and to model the effects of cross and/or head winds near the ground. The present results show the influences of various parameters on the aerodynamic coefficients for both steady and unsteady flows. Generally, the ground increases the aerodynamic coefficients; the greater the sink rates, the stronger the effects. Increasing the aspect ratio increases both the steady and unsteady ground effects. An exception is a large aspect-ratio wing with large camber. The present results are generally in close agreement with limited exact solutions and experimental data. In the aerodynamic-dynamic simulation, the equations of motion were solved by Hammlng's predictor-corrector method. The aircraft, air stream, and control surfaces were treated as a single dynamic system. The entire set of governing equations was solved simultaneously and interactively. The aerodynamic-dynamic model was used to study a configuration that resembles a Cessna 182 airplane. The ground lowers the effectiveness of the tail in controlling pitch, increases the lift and drag, and makes the hinge-moment less negative. Proportional and rate control laws were used in a feedback system to control pitch. One set of gains was used in and out of ground effect. For the same control input, the pitch angle responds faster and overshoots more near the ground than it does far from the ground. The present results demonstrate the feasibility of using the current simulation to model more complicated motions and the Importance of including the unsteady ground effects when analyzing the performance of an airplane during a landing maneuver. / Ph. D. LD5655.V856 1988.N842 Runways (Aeronautics) -- Testing Airplanes -- Landing Airplanes -- Takeoff
3	Reverse Engineering of Passenger Jets - Classified Design Parameters De Grave, Emiel January 2017 (has links) (PDF) This thesis explains how the classified design parameters of existing passenger jets can be determined. The classified design parameters are; the maximum lift coefficient for landing and take-off, the maximum aerodynamic efficiency and the specific fuel consumption. The entire concept is based on the preliminary sizing of jet powered civil aeroplanes. This preliminary sizing is explained in detail because it is the foundation of the final result. The preliminary sizing is combined using reverse engineering which is not a strict method. Therefore, only the basics are explained. By applying reverse engineering on the preliminary sizing and aiming for the classified design parameters as output, formulas are derived to calculate the maximum lift coefficients, the maximum aerodynamic efficiency and the specific fuel consumption. The goal is to calculate these parameters, using only aircraft specifications that are made public by the manufacturer. The calculations are complex with mutual relations, iterative processes and optimizations. Therefore, it is interesting to integrate everything in a tool. The tool is built in Microsoft Excel and explained in detail adding operating instructions. The program is executed for miscellaneous aeroplanes, supported with the necessary comments. Investigated aeroplanes are: Caravelle 10B (Sud-Aviation), Boeing 707-320C, BAe 146-200 (British Aerospance), A320-200 (Airbus), "The Rebel" (based on A320), Boeing SUGAR High, Boeing 747-400, Blended Wing Body VELA 2 (VELA) and Dassault Falcon 8X. ddc:620 info:eu-repo/classification/ddc/629.13 Luftfahrt Luftfahrzeug Passagierflugzeug Reverse Engineering Aeronautics Airplanes Design Reverse engineering Luftfahrttechnik Luftfahrzeug Passagierflugzeug Reverse Engineering Luftfahrttechnik Aerodynamik Passagier Flugzeug Entwurf Dimensionierung Verifikation Kraftstoffverbrauch Start Landung Reiseflug Gleitzahl Auftriebsbeiwert Aeronautics Airplanes Design Reverse engineering Aerodynamics Aeroplanes Computer software Electronic Spreadsheets Verification (Logic) Airplanes--Fuel Consumption Lift (Aerodynamics) Airplanes-Takeoff Airplanes-Landing Preliminary sizing Glide ratio L/D Cruise

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