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Thesis (M.S.)--California Polytechnic State University, 2008. / Mode of access: Internet. Title from PDF title page; viewed on March 17, 2009. Major professor: David D. Marshall. "Presented to the faculty of California Polytechnic State University, San Luis Obispo." "In partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering." "June 2008." Includes bibliographical references (p. 126-127). Also available on microfiche.

Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2007. / Dimitri N. Mavris, Committee Chair ; Lakshmi N. Sankar, Committee Member ; Daniel P. Schrage, Committee Member ; Robert J. Englar, Committee Member ; Robert C. Michelson, Committee Member.

This thesis is an examination of the problems that may arise from the location of S.T.O.L. airports within urbanized areas. The role of air transportation as a passenger travel mode is considered and the problems facing the existing air transportation system are explored. The potential role of S.T.O.L. aircraft within the air transportation system is examined in detail. Additionally, the benefits that may accrue from the use of S.T.O.L. aircraft in a regional air transport system are discussed extensively. The criteria to be used when looking for potential S.T.O.L. airport sites are examined in detail. These criteria are applied to three potential S.T.O.L. airport sites within the Vancouver urban area. In some cases the locational criteria were found to be difficult to operationalize. Data on community reaction to noise exposure is inadequate and noise standards are difficult to apply on a wide basis. The concept of land use compatibility around airports is useful but only to the extent that it does not obscure the fact that aircraft operations can cause community disruptions beyond the boundaries of the so-called compatible land uses. With specific reference to Vancouver, the available data indicates, that on the average, very little terminal access or egress time will be saved if a S.T.O.L. airport were built at a suitable location between the existing airport and the downtown area. Finally, the paper concludes by suggesting that despite the fact that S.T.O.L. aircraft cannot bring substantial time savings to regional air passengers, a S.T.O.L. air service may mean that many of the regions under utilized conventional airports could be converted to S.T.O.L. airports and yeild substantial savings in the money used to maintain and operate the publically owned airports in the province. / Applied Science, Faculty of / Community and Regional Planning (SCARP), School of / Graduate

The rapid air travel growth during the last three decades, has resulted in runway congestion at major airports. The current airports infrastructure will not be able to support the rapid growth trends expected in the next decade. Changes or upgrades in infrastructure alone would not be able to satisfy the growth requirements, and new airplane concepts such as the NASA proposed Super Short Takeo and Landing and Extremely Short Takeo and Landing (ESTOL) are being vigorously pursued. Aircraft noise pollution during Takeoff and Landing is another serious concern and efforts are aimed to reduce the airframe noise produced by Conventional High Lift Devices during Takeoff and Landing. Circulation control technology has the prospect of being a good alternative to resolve both the aforesaid issues. Circulation control airfoils are not only capable of producing very high values of lift (Cl values in excess of 8.0) at zero degree angle of attack, but also eliminate the noise generated by the conventional high lift devices and their associated weight penalty as well as their complex operation and storage. This will ensure not only satisfying the small takeoff and landing distances, but minimal acoustic signature in accordance with FAA requirements. The Circulation Control relies on the tendency of an emanating wall jet to independently control the circulation and lift on an airfoil. Unlike, conventional airfoil where rear stagnation point is located at the sharp trailing edge, circulation control airfoils possess a round trailing edge, therefore the rear stagnation point is free to move. The location of rear stagnation point is controlled by the blown jet momentum. This provides a secondary control in the form of jet momentum with which the lift generated can be controlled rather the only available control of incidence (angle of attack) in case of conventional airfoils. The use of Circulation control despite its promising potential has been limited only to research applications due to the lack of a simple prediction capability. This research effort was focused on the creation of a rapid prediction capability of Circulation Control Aerodynamic Characteristics which could help designers with rapid performance estimates for design space exploration. A morphological matrix was created with the available set of options which could be chosen to create this prediction capability starting with purely analytical physics based modeling to high fidelity CFD codes. Based on the available constraints, and desired accuracy metamodels has been created around the two dimensional circulation control performance results computed using Navier Stokes Equations (Computational Fluid Dynamics). DSS2, a two dimensional RANS code written by Professor Lakshmi Sankar was utilized for circulation control airfoil characteristics. The CFD code was first applied to the NCCR 1510-7607N airfoil to validate the model with available experimental results. It was then applied to compute the results of a fractional factorial design of experiments array. Metamodels were formulated using the neural networks to the results obtained from the Design of Experiments. Additional validation runs were performed to validate the model predictions. Metamodels are not only capable of rapid performance prediction, but also help generate the relation trends of response matrices with control variables and capture the complex interactions between control variables. Quantitative as well as qualitative assessments of results were performed by computation of aerodynamic forces and moments and flow field visualizations. Wing characteristics in three dimensions were obtained by integration over the whole wing using Prandtl's Wing Theory. The baseline Super STOL configuration was then analyzed with the application of circulation control technology. The desired values of lift and drag to achieve the target values of Takeoff and Landing performance were compared with the optimal configurations obtained by the model. The same optimal configurations were then subjected to Super STOL cruise conditions to perform a tradeoff analysis between Takeoff and Cruise Performance. Supercritical airfoils modified for circulation control were also thoroughly analyzed for Takeoff and Cruise performance and may constitute a viable option for Super STOL and STOL Designs. The prediction capability produced by this research effort can be integrated with the current conceptual aircraft modeling and simulation framework. The prediction tool is applicable within the selected ranges of each variable, but methodology and formulation scheme adopted can be applied to any other design space exploration.

Thesis (M.S.)--California Polytechnic State University, 2009. / Title from PDF title page; viewed on June 11, 2009. "May 2009." "In partial fulfillment of the requirements for the degree [of] Master of Science in Aerospace Engineering." "Presented to the faculty of California Polytechnic State University, San Luis Obispo." Major professor: Daniel Biezad, Ph.D. Includes bibliographical references (p. 78-79). Also available on microfiche.

Thesis (M.S.)--California Polytechnic State University, 2010. / Title from PDF title page; viewed on May 20, 2010. Major professor: David Marshall, Ph.D. "Presented to the faculty of California Polytechnic State University, San Luis Obispo." "In partial fulfillment of the requirements for the degree [of] Master of Science in Aerospace Engineering." "April 2010." Includes bibliographical references (p. 80-82).