Numerical Investigation of the Aerodynamic and Infrared Radiation Characteristics of Spherical Convergent Flap Nozzles
Publication: Journal of Aerospace Engineering
Volume 29, Issue 5
Abstract
A number of numerical predictions are performed to evaluate the aerodynamic and infrared radiation characteristics of spherical convergent flap nozzles (SCFN). The accuracy of the computations was verified by comparing the calculated wall pressure values to experimentally measured ones. The prediction results show that the vortices produced by the secondary flow at the corner of the divergent section are the main factor to produce thrust loss without any vectoring action. Compared to the axisymmetric nozzle, the SCFN caused up to 1.86% thrust loss and 3% flow rate loss. The yaw angle had no effect on the inner flow field in the divergent section and the exhaust flow because the yaw vector turning is achieved by gimballed subsonic flow. The maximum thrust losses were only 1 and 0.69%, which were caused by the pitch and yaw vector, respectively. The aerodynamic vector angle was approximately consistent with the turning angle due to geometric deflection of SCFN. With a 15° geometric pitch angle, the maximum radiation was depressed by 8.76% on the vertical plane and by 23.9% on the horizontal plane relative to that without pitch. With a 10° geometric yaw angle, the maximum radiation was depressed by 11.8 and 5.7 on the horizontal and vertical planes, respectively.
Get full access to this article
View all available purchase options and get full access to this article.
Acknowledgments
The authors gratefully acknowledge financial support for this project from the Fundamental Research Funds for the Central Universities (No. NS2014018) and the Natural Science Foundation of Jiangsu Province (No. BK20130790).
References
Berrier, B. L., Taylor, J. G. (1990). “Internal performance of two nozzles utilizing gimbal concepts for thrust vectoring.” NASA TP-2991.
Capone, F. J., and Deere, K. A. (2001). “Transonic investigation of two-dimensional nozzles designed for supersonic cruise.”, AIAA, Reston, VA, 2001–3199.
Carlson, J. R., and Abdol-Hamid, K. S. (1991). “Prediction of internal performance for two-dimensional convergent-divergent nozzles.” AIAA-91-2369, AIAA, Reston, VA.
Celik, I. B., Ghia, U., Roache, P. J., Freitas, C. J., Coleman, H., and Raad, P. E. (2008). “Procedure for estimation and reporting of uncertainty due to discretization in CFD applications.” J. Fluids Eng., 130(7), 078001.
Cheatham, P. L., Walker, S. H., and Gridley, M. C. (1990). “Computation of vectoring nozzle performance.” AIAA-90-2752, AIAA, Reston, VA.
Cler, D. L., Mason, M. L., and Guthrie, A. R. (1993). “Experimental investigation of spherical convergent-flap thrust-vectoring two dimensional plug nozzles.” AIAA 93–2431, AIAA, Reston, VA.
Gutierrez, J. L., Davis, C. L., and Hawkes, T. M. (1995). “First full-scale engine evaluation of an IHPTET exhaust nozzle technology demonstrator.” AIAA 95–2747, AIAA, Reston, VA.
Ikaza, D. (2000). “Thrust vectoring nozzle for modern military aircraft.” RTO A VT Symposium on "Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles, RTO.
Jin, J., Zhao, J. Y., Zhang, M. H., and Lai, C. X. (2000). “Experimental investigation of static internal performance for an axisymmetric vectoring exhaust nozzle.” ICAS 2000 Congress, 534-1–534-7.
Meyer, B. E., and MacLean, M. K. (1993). “Scale model test results for several spherical/two-dimensional nozzle concepts.” AIAA 93–2430, AIAA, Reston, VA.
Shan, Y., and Zhang, J. Z. (2009). “Numerical investigation of flow mixture enhancement and infrared radiation shield by lobed forced mixer.” Appl. Therm. Eng., 29(17–18), 3687–3695.
Syed, S. A., Erhart, J. J., and King, E. W. (1990). “Application of CFD to pitch/yaw thrust vectoring spherical convergent flap nozzles.” AIAA 90–2023, AIAA, Reston, VA.
Syed, S. A., Erhart, J. J., and King, E. W. (1992). “Application of computational fluid dynamics to pitch/yaw thrust vectoring spherical convergent flap nozzles.” J. Propul. Power, 8(4), 799–805.
Wilson, E. A., Adler, D., and Bar-Yoseph, P. (2003). “Thrust-vectoring nozzle performance modeling.” J. Propul. Power, 19(1), 39–47.
Wing, D. J. (1998). “Static thrust and vectoring performance of a spherical convergent flap nozzle with a nonrectangular divergent duct.” NASA/TP-1998-206912.
Wing, D. J., and Capone, F. J. (1993). “Performance characteristics of two multiaxis thrust-vectoring nozzles at Mach numbers up to 1.28.” NASA.
Zhang, J. Z, Xie, Z. R., and Zheng, L. B. (2004). “Experimental investigation on hot-jet characteristics of 2-D convergent-divergent vector nozzles.” Gas Turb. Exp. Res., 17(3), 6–9.
Information & Authors
Information
Published In
Copyright
© 2016 American Society of Civil Engineers.
History
Received: Mar 4, 2015
Accepted: Aug 20, 2015
Published online: Apr 25, 2016
Published in print: Sep 1, 2016
Discussion open until: Sep 25, 2016
Authors
Metrics & Citations
Metrics
Citations
Download citation
If you have the appropriate software installed, you can download article citation data to the citation manager of your choice. Simply select your manager software from the list below and click Download.