Author: Paul J. BarnhartPublisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
NPAC-Nozzle Performance Analysis Code
Author: Paul J. BarnhartNpac-nozzle Performance Analysis Code Final Report ... Nasa-cr-204129 ... Oct. 20, 1997
Author: Static Performance of a Fixed-Geometry Exhaust Nozzle Incorporating Porous Cavities for Shock-Boundary Layer Interaction Control
Author: Scott C. AsburyPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 142
Book Description
Research & Technology 1997
Author: Publisher: DIANE Publishing
ISBN: 1428918256
Category :
Languages : en
Pages : 190
Book Description
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Effects of Convoluted Divergent Flap Contouring on the Performance of a Fixed-Geometry Nonaxisymmetric Exhaust Nozzle
Author: Scott C. AsburyPerformance Analysis of an Axisymmetric Thrust-vectoring Nozzle by Using the FUNSIF3-D Code
Author: A. MatesanzMonthly Catalog of United States Government Publications
Author: Research and Technology 1997
Author: A Prediction Code for the Thrust Performance of Two-Dimensional, Non-Axisynnetric, Converging Diverging Nozzles
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 119
Book Description
The objective of this research is to develop a prediction code for the Air Force Research Laboratory Propulsion Directorate that can accurately determine the gross thrust coefficient for a user defined nonaxisymmetric two-dimensional converging diverging nozzle. The code includes the effects of friction, angularity, and expansion losses on nozzle efficiency. To demonstrate the prediction method, the generated computational results were compared to experimental data, as well as computational results from other existing nozzle performance codes, for a number of different nozzle geometries. The nozzle internal performance prediction code showed excellent agreement with experimental data in predicting the gross thrust performance for all nozzle geometries considered. It was shown, however, that when the experimental data showed evidence of flow separation, a flow phenomenon this code is unable to predict, the code results underpredicted the experimental by up to 10%.