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   <dim:field mdschema="dc" element="contributor" qualifier="advisor" lang="en_US">Alan H. Epstein.</dim:field>
   <dim:field mdschema="dc" element="contributor" qualifier="author" lang="en_US">Al-Essa, Fouzi Khalid Sultan, 1970-</dim:field>
   <dim:field mdschema="dc" element="contributor" qualifier="department">Massachusetts Institute of Technology. Department of Mechanical Engineering</dim:field>
   <dim:field mdschema="dc" element="date" qualifier="accessioned">2009-06-30T17:17:47Z</dim:field>
   <dim:field mdschema="dc" element="date" qualifier="available">2009-06-30T17:17:47Z</dim:field>
   <dim:field mdschema="dc" element="date" qualifier="copyright" lang="en_US">1997</dim:field>
   <dim:field mdschema="dc" element="date" qualifier="issued" lang="en_US">1997</dim:field>
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   <dim:field mdschema="dc" element="identifier" qualifier="oclc" lang="en_US">38529436</dim:field>
   <dim:field mdschema="dc" element="description" lang="en_US">Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1997.</dim:field>
   <dim:field mdschema="dc" element="description" lang="en_US">Includes bibliographical references (p. 127-128).</dim:field>
   <dim:field mdschema="dc" element="description" qualifier="statementofresponsibility" lang="en_US">by Fouzi Khalid Sultan Al-Essa.</dim:field>
   <dim:field mdschema="dc" element="description" qualifier="degree" lang="en_US">M.S.</dim:field>
   <dim:field mdschema="dc" element="format" qualifier="extent" lang="en_US">134 p.</dim:field>
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copyright. They may be viewed from this source for any purpose, but 
reproduction or distribution in any format is prohibited without written 
permission. See provided URL for inquiries about permission.</dim:field>
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   <dim:field mdschema="dc" element="subject" lang="en_US">Mechanical Engineering</dim:field>
   <dim:field mdschema="dc" element="title" lang="en_US">An experimental study of compressor stability in a 450 kW helicopter gas turbine engine</dim:field>
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   	&lt;Title>An experimental study of compressor stability in a 450 kW helicopter gas turbine engine&lt;/Title>
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