<div class="description">
<dl><dd>Cover title: Determination ... maximum flux and enthaply profiles for a very high ..</dd>
<dd>ADA218390</dd>
<dd>Thesis advisor, Richard D. Wood</dd>
<dd>Thesis (M.S. in Aero. Eng.) Naval Postgraduate School, June 1989</dd>
<dd>Includes bibliographical references</dd>
<dd>Hypervelocity flows for velocities is excess of 1.4 km/sec (Mach 5) require very high stagnation temperature to avoid liquefaction. The arc heater wind tunnel has been designed to provide such flows. The electric-are driven wind tunnel can develop stagnation temperatures up to 13,000 K which will produce hypervelocity flows up to 7 km/sec (earth orbital speed). The nature of the flow, however, is such that the high temperature source flow may cause severe gradients at the nozzle exit. In order to perform aero-thermodynamic tests the characterization of the flow in the test section is required. This paper experimentally determines the stream profiles for an arcjet wind tunnel conical nozzle directly from calorimetry and pitot probe surveys. Keywords: Arcjet flow; Hypervelocity flow; High enthalpy flow; Flow characteristics; Characteristic profile of the flow;</dd></dl><br>Subjects: Fluid mechanics; Arc-jet rocket engines; Nozzles; Fluid dynamics; Hypersonic wind tunnels; Test gases</div>
<div class="fn value">
Kopp, Robert William.</div>
Internet Archive identifier