Performance Analysis of an Axisymmetric Thrust-vectoring Nozzle by Using the FUNSIF3-D Code PDF Download

Author: A. Matesanz
Publisher:
ISBN:
Category :
Languages : en
Pages :

View

Book Description

Author: John S. Orme
Publisher:
ISBN:
Category : Black Widow (Night fighter plane)
Languages : en
Pages : 26

View

Book Description
A full envelope database of a thrust-vectoring axisymmetric nozzle perfomance for the Pratt & Whitney Pitch/Yaw Balance Beam Nozzle (P/YBBN) is being developed using the F-15 Advanced Control Technology for Integrated Vehicles (ACTIVE) aircraft. At this time, flight research has been completed for steady-state pitch vector angles up to 20 deg. at an altitude of 30,000 ft from low power settings to maximum afterburner power. The nozzle performance database includes vector forces, internal nozzle pressures, and temperatures all of which can be used for regression analysis modeling. The database was used to substantiate a set of nozzle performance data from wind tunnel testing and computational fluid dynamic analyses. Findings from initial flight research at Mach 0.9 and 1.2 are presented in this paper. The results show that vector efficiency is strongly influenced by power setting. A significant discrepancy in nozzle performance has been discovered between predicted and measured results during vectoring.

Author: Bret D. Clark
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 146

View

Book Description
This research project was a study of cold-jet thrust vectored nozzle performance utilizing 1/32 scale models of F-15 axisymmetric nozzles.

Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781724005533
Category : Science
Languages : en
Pages : 28

View

Book Description
Flight tests recently completed at the NASA Dryden Flight Research Center evaluated performance of a hydromechanically vectored axisymmetric nozzle onboard the F-15 ACTIVE. A flight-test technique whereby strain gages installed onto engine mounts provided for the direct measurement of thrust and vector forces has proven to be extremely valuable. Flow turning and thrust efficiency, as well as nozzle static pressure distributions were measured and analyzed. This report presents results from testing at an altitude of 30,000 ft and a speed of Mach 0.9. Flow turning and thrust efficiency were found to be significantly different than predicted, and moreover, varied substantially with power setting and pitch vector angle. Results of an in-flight comparison of the direct thrust measurement technique and an engine simulation fell within the expected uncertainty bands. Overall nozzle performance at this flight condition demonstrated the F100-PW-229 thrust-vectoring nozzles to be highly capable and efficient. Orme, John S. and Sims, Robert L. Armstrong Flight Research Center H-2339, ISABE Paper 1S-166

Author: George T. Carson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 84

View

Book Description

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724261922
Category :
Languages : en
Pages : 232

View

Book Description
A series of thrust-vectored axisymmetric ejector nozzles were designed and experimentally tested for internal performance and pumping characteristics at the Langley research center. This study indicated that discontinuities in the performance occurred at low primary nozzle pressure ratios and that these discontinuities were mitigated by decreasing expansion area ratio. The addition of secondary flow increased the performance of the nozzles. The mid-to-high range of secondary flow provided the most overall improvements, and the greatest improvements were seen for the largest ejector area ratio. Thrust vectoring the ejector nozzles caused a reduction in performance and discharge coefficient. With or without secondary flow, the vectored ejector nozzles produced thrust vector angles that were equivalent to or greater than the geometric turning angle. With or without secondary flow, spacing ratio (ejector passage symmetry) had little effect on performance (gross thrust ratio), discharge coefficient, or thrust vector angle. For the unvectored ejectors, a small amount of secondary flow was sufficient to reduce the pressure levels on the shroud to provide cooling, but for the vectored ejector nozzles, a larger amount of secondary air was required to reduce the pressure levels to provide cooling. Lamb, Milton Langley Research Center NASA-TM-4610, L-17386, NAS 1.15:4610 RTOP 505-59-30-04...

Author: Bobby L. Berrier
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 62

View

Book Description

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722772215
Category :
Languages : en
Pages : 52

View

Book Description
An investigation was conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to determine the flow-turning capability and the nozzle internal performance of an axisymmetric convergent-divergent nozzle with post-exit vanes installed for multiaxis thrust vectoring. The effects of vane curvature, vane location relative to the nozzle exit, number of vanes, and vane deflection angle were determined. A comparison of the post-exit-vane thrust-vectoring concept with other thrust-vectoring concepts is provided. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 1.6 to 6.0. Berrier, Bobby L. and Mason, Mary L. Langley Research Center...

Author: Laurence D. Leavitt
Publisher:
ISBN:
Category : Jet planes
Languages : en
Pages : 28

View

Book Description

Author: David J. Wing
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 88

View

Book Description