Heat Transfer Model of a Jet Pump Cowl Anti-Ice System

965524

10/01/1996

Event
World Aviation Congress & Exposition
Authors Abstract
Content
A theoretical heat transfer model was applied in the design and performance prediction of an aircraft nozzle cowl anti-ice system. Laboratory heat transfer tests were conducted to determine nozzle performance in a curved D-duct specimen. The local convective film coefficient variation on the interior nose cowl surface was empirically fitted relative to the secondary flow parameters in the D-duct. The measured D-duct flow variables were in excellent agreement with the theoretical jet pump model calculations, allowing the model to predict the internal heat transfer coefficient anywhere inside the nose cowl and calculate steady state skin temperature profiles during anti-icing.
By minimizing the predicted thickness of runback ice aft of the heated cowl surface, an optimum nozzle design was determined analytically. The predicted anti-ice performance of the nose cowl ice protection design was later verified by flight test measurements of nose cowl skin temperatures.
Meta TagsDetails
DOI
https://doi.org/10.4271/965524
Pages
17
Citation
Kim, J., "Heat Transfer Model of a Jet Pump Cowl Anti-Ice System," SAE Technical Paper 965524, 1996, https://doi.org/10.4271/965524.
Additional Details
Publisher
Published
Oct 1, 1996
Product Code
965524
Content Type
Technical Paper
Language
English