Effect of free boundary on the performance of single expansion nozzle
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Dakshina Murthy Inturi
,
Lovaraju Pinnam
and
Ramachandra Raju Vegesna
Abstract
Effect of free boundary on the flow field characteristics of a single expansion nozzle has been studied experimentally and computationally. The single expansion nozzles studied in this investigation are a convergent-divergent nozzle of rectangular cross-section with convergent-divergent wall on one side and a flat wall on the opposite side, and an identical convergent-divergent ramp with its top open to atmosphere. The studies have been carried out at nozzle pressure ratios 2, 3, 4 and 5. The results show that the single expansion nozzle with wall boundary is able to deliver the flow with Mach number around 1.5, at nozzle pressure ratios of 4 and 5 even with the single expansion. The nozzle with free boundary, the wall static pressure is appreciably lower than that of nozzle with closed boundary and the exit Mach number is 1.5 for NPR 4 and 1.75 for NPR 5. That is, at the exit, the single expansion nozzle with free boundary delivers higher Mach number compared to single expansion nozzle with wall boundary for NPR 5.
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Author contribution: This research is the outcome of joint effort. All authors have read and approved the final manuscript.
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Research funding: No funding/grants received for this research work.
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Conflict of interest statement: The authors declare that they have no conflict interests.
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Availability of data and materials: The datasets used and/or analysed during the current study are available from the corresponding author on reasonable request.
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Articles in the same Issue
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Articles in the same Issue
- Frontmatter
- Numerical investigations of heat transfer characteristics using oblong fins and circular fins in a wedge channel
- An efficient flow control technique based on co-flow jet and multi-stage slot circulation control applied to a supercritical airfoil
- Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity
- Installed performance seeking control based on supersonic variable inlet/engine coupling model
- Effect of zero penetration angle chevrons in supersonic jet noise and screech tone mitigation
- The aerodynamic performance degradation analysis of a small high bypass turbofan engine compression system with fan rotor blade leading edge erosion
- Flow structure comparison of film cooling versus hybrid cooling: a CFD study
- Experimental investigation on a Jeffcott rotor with combined coupling misalignment using time-frequency analysis
- Effect of free boundary on the performance of single expansion nozzle
- Optimization and numerical investigation of combined design of blade and endwall on rotor 67
- Numerical study on the effect of distortion of S-duct on flow field and performance of a full annulus transonic fan
- Research on a high-precision real-time improvement method for aero-engine component-level model
- Uncertainty quantification by probabilistic analysis of circular fins
- Influences of unbalance phase combination on the dynamic characteristics for a turboprop engine
- Study on the water ingestion performance of compressor with inlet particle separator
- The role of volume effect on the transient behavior of a transonic compressor
- Experimental analysis of performance and tip dynamic pressure in a compressor cascade with high-speed moving endwall
- Numerical study of the impact of hydrogen addition, swirl intensity and equivalence ratio on methane-air combustion
- Active subspace-based performance analysis of supersonic through-flow fan rotor
- Assessment of performance degradation of a mixed flow low bypass turbofan engine through GasTurb simulation
- Numerical investigation of tip clearance flow in a variable geometry turbine with non-uniform partial clearance
