<div class="description">
<dl><dd>Title from cover</dd>
<dd>"Prepared for: Naval Air Systems Command"--Cover</dd>
<dd>"May 1981"--Cover</dd>
<dd>"NPS67-81-008"--Cover</dd>
<dd>DTIC Identifiers: Blade tips, PE61153N</dd>
<dd>Author(s) key words: Axial compressor blading, radial equilibrium</dd>
<dd>Includes bibliographical references (p. 9)</dd>
<dd>Technical report; 1981</dd>
<dd>A computer program was used to calculate the radial distribution of flow parameters in an axial compressor stage designed to have a symmetrical velocity diagram at the mean radius and particular variations of reaction from hub to tip. Uniform energy addition was assumed to occur in the rotor. Both cases of uniform enthalpy and uniform radial enthalpy gradient at the entrance to the stage were considered. Advantages were found in the selection of fully symmetric blading and in the use of the inlet enthalpy gradient as a design parameter. (Author)</dd>
<dd>kmc/kmc 10/23/09</dd></dl><br>Subjects: AIRPLANES--RAMJET ENGINES--COMBUSTION--MATHEMATICAL MODELS; SOLID PROPELLANTS--COMBUSTION</div>
<div class="fn value">
Schlachter, W</div>
Internet Archive identifier