Author: John R. CarlsonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 56
Book Description
A Nozzle Internal Performance Prediction Method
Author: John R. CarlsonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 56
Book Description
A Nozzle Internal Performance Prediction Method
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722140021
Category :
Languages : en
Pages : 52
Book Description
A prediction method was written and incorporated into a three-dimensional Navier-Stokes code (PAB3D) for the calculation of nozzle internal performance. The following quantities are calculated: (1) discharge coefficient; (2) normal, side, and axial thrust ratios; (3) rolling, pitching, and yawing moments; and (4) effective pitch and yaw vector angles. Four different case studies are presented to confirm the applicability of the methodology. Internal and, in most situations, external flow-field regions are required to be modeled. The computed nozzle discharge coefficient matches both the level and the trend of the experimental data within quoted experimental data accuracy (0.5 percent). Moment and force ratios are generally within 1 to 2 percent of the absolute level of experimental data, with the trends of data matched accurately. Carlson, John R. Langley Research Center...
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%.
A Method for the Prediction of Exhaust Nozzle Performance
Author: William John YeagerPublisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 298
Book Description
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 376
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.
Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90
Author: John R. CarlsonPublisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 32
Book Description
NASA Scientific and Technical Publications
Author: NASA Scientific and Technical Publications: A Catalog of Special Publications, Reference Publications, Conference Publications, and Technical Papers, 1991-1992
Author: Prediction methods for jet V/STOL propulsion aerodynamics
Author: Max PlatzerExperimental and Analytical Determination of Integrated Airframe Nozzle Performance
Author: Edsel R. GlasgowPublisher:
ISBN:
Category : Airframes
Languages : en
Pages : 142
Book Description
A computer program has been developed for predicting twin-nozzle/aftbody drag and internal nozzle performance for fighter type aircraft having twin buried engines and dual nozzles. The program is capable of generating the installed thrust-minus-drag data required for conducting mission analysis studies of aircraft of this type. The configuration variables which can be analyzed include (1) nozzle type (convergent flap and iris, convergent-divergent with and without secondary flow, and shrouded and unshrouded plug), (2) nozzle lateral spacing, (3) interfairing type (horizontal and vertical wedge), (4) interfairing length, and (5) vertical stabilizer type (single and twin). The performance prediction methods incorporated in the program are based almost entirely on empirical correlations. Specifically, correlations used in conjunction with one-dimensional flow relationships are employed for the prediction of the nozzle thrust and discharge coefficients, and correlations of the test data obtained during the contracted effort are employed for prediction of the aft-end drag. The prediction methods account for the effects of nozzle pressure ratio and flow separation on both internal and external nozzle surfaces. This manual describes the operation of the computer program in terms of program input requirements, performance prediction methods, and output format and includes a presentation of sample input/output cases and a complete computer listing of the program. The program has been developed for use on the CDC 6600 computer.