Heat transfer in a complex trailing edge passage for a high pressure turbine blade.

Heat transfer in a complex trailing edge passage for a high pressure turbine blade. Pt. 2, Simulation results [microform] / David L. Rigby, Ronald S. Bunker.

Saved in:

Bibliographic Details
Online Access:	Connect to online resource Connect to online resource
Main Author:	Rigby, D. L. (David Lester), 1963-
Corporate Author:	NASA Glenn Research Center
Other Authors:	Bunker, Ronald S.
Other title:	Simulation results.
Format:	Government Document Microfilm Book
Language:	English
Published:	[Cleveland, Ohio] : Hanover, MD : National Aeronautics and Space Administration, Glenn Research Center ; Available from NASA Center for Aerospace Information, [2002]
Series:	NASA contractor report ; NASA CR-211701.
Subjects:	Trailing edges. Turbine blades. Computerized simulation. High pressure. Heat transfer coefficients. Three dimensional flow.

Internet

Connect to online resource
Connect to online resource

Norlin Library - Government Information - Microform

Holdings details from Norlin Library - Government Information - Microform
Call Number:	NAS 1.26:211701
NAS 1.26:211701	Restricted Place a Hold

Online

Holdings details from Online
Call Number:	NAS 1.26:211701
NAS 1.26:211701	Available