Analysis and Parameter Estimation of the Aerodynamic and Handling Qualities of the C-130A Modified With Wing Tip Tanks

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dc.contributor.advisor Dr. Charles E. Hall Jr., Committee Chair en_US
dc.contributor.advisor Dr. Ashok Gopalarathnam, Committee Member en_US
dc.contributor.advisor Dr. James Selgrade, Committee Member en_US
dc.contributor.author Phillips, David en_US
dc.date.accessioned 2010-04-02T17:57:45Z
dc.date.available 2010-04-02T17:57:45Z
dc.date.issued 2004-12-02 en_US
dc.identifier.other etd-11302004-185835 en_US
dc.identifier.uri http://www.lib.ncsu.edu/resolver/1840.16/691
dc.description.abstract This work presents the background, flight testing, and resulting change in the aerodynamic and handling qualities of a C-130A Hercules modified with wing tip tanks. The data collected during the baseline and modified flight tests of this aircraft demonstrated the potential aerodynamic benefits of a tip tank design that incorporates a greater aspect ratio and end plating effects. Wing mounted pressure belts measured a 24% increase in local Cl near the tip tanks. This local increase in lift contributed to a 38% increase in CL max for the airplane. The pressure and dynamic data was gathered using a LIFT (Linux In Flight Testing) system, and it laid the foundation for finding the longitudinal and lateral directional stability coefficients of the airplane. Then using MATLAB® and the System IDentification Programs for AirCraft (SIDPAC) to reduce this data, it was possible to generate aerodynamic, lateral, and longitudinal parameters that clearly proved the overall benefits of the design change. The demonstrated lift benefits of these uniquely designed tip tanks for the C-130A cargo transport proved that by capitalizing on the benefits of a combination tip tank and end plate design it is possible to generate increased lift without adversely affecting the stability and dynamic parameters of the aircraft. en_US
dc.rights I hereby certify that, if appropriate, I have obtained and attached hereto a written permission statement from the owner(s) of each third party copyrighted matter to be included in my thesis, dissertation, or project report, allowing distribution as specified below. I certify that the version I submitted is the same as that approved by my advisory committee. I hereby grant to NC State University or its agents the non-exclusive license to archive and make accessible, under the conditions specified below, my thesis, dissertation, or project report in whole or in part in all forms of media, now or hereafter known. I retain all other ownership rights to the copyright of the thesis, dissertation or project report. I also retain the right to use in future works (such as articles or books) all or part of this thesis, dissertation, or project report. en_US
dc.subject flying qualties en_US
dc.subject flight test en_US
dc.subject end plate en_US
dc.subject tip tank en_US
dc.subject aerodynamic en_US
dc.title Analysis and Parameter Estimation of the Aerodynamic and Handling Qualities of the C-130A Modified With Wing Tip Tanks en_US
dc.degree.name MS en_US
dc.degree.level thesis en_US
dc.degree.discipline Aerospace Engineering en_US


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