Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
-
Lei Shi
,
Xiaowei Liu
Abstract
Numerical integration simulations were performed on a ready-made central strut-based rocket-based combined-cycle (RBCC) engine operating in the ejector mode during the takeoff regime. The effective principles of various cowl lip positions and shapes on the inlet operation and the overall performance of the entire engine were investigated in detail. Under the static condition, reverse cowl lip rotation in a certain range was found to contribute comprehensive improvement to the RBCC inlet and the entire engine. However, the reverse rotation of the cowl lip contributed very little enhancement of the RBCC inlet under the low subsonic flight regime and induced extremely negative impacts in the high subsonic flight regime, especially in terms of a significant increase in the drag of the inlet. Changes to the cowl lip shape provided little improvement to the overall performance of the RBCC engine, merely shifting the location of the leeward area inside the RBCC inlet, as well as the flow separation and eddy, but not relieving or eliminating those phenomena. The results of this study indicate that proper cowl lip rotation offers an efficient variable geometry scheme for a RBCC inlet in the takeoff regime.
Funding statement: Funding: This work was supported by the Fundamental Research Funds for the Central Universities (No.3102015ZY006), and Shanghai Key Laboratory of Multiphase Flow and Heat Transfer in Power Engineering.
Nomenclature
- Da
aberration degree of flow at the exit of RBCC inlet
- Dinlet
drag of RBCC inlet, obtained from a force integration over all of the inner walls and external cowl lip wall, N
- Fcom
overall inner thrust of RBCC combustor, N
- Fengine
overall inner thrust of RBCC engine, obtained from a force integration over all of the inner walls and external cowl lip wall, N
- Hc
capture height of RBCC inlet, mm
- He
height of the exit of RBCC engine, mm
- H∞
flight height, km
- mair
mass flow rate of entrained air, kg/s
- M∞
flight Mach number
- Mout
Mach number at exit of RBCC inlet
- mrocket
mass flow rate of gas in embedded rocket engine, kg/s
- Mstart
starting Mach number of RBCC inlet
- MR
mixing ratio (oxygen-to-fuel, O/F) of rocket
- P
static pressure along flowpath, Pa
- P0
total pressure of incoming flow, Pa
- Φ
entraining ratio of secondary flow (air)
- σ
total pressure recovery coefficient of RBCC inlet
- W
width of the RBCC engine, mm
- x
x-value along flow path, mm
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©2016 by De Gruyter
Artikel in diesem Heft
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
Artikel in diesem Heft
- Frontmatter
- Experimental Investigation on the Ignition Delay Time of Plasma-Assisted Ignition
- Effect of Inlet Clearance on the Aerodynamic Performance of a Centrifugal Blower
- Alternative Method to Simulate a Sub-idle Engine Operation in Order to Synthesize Its Control System
- Aerodynamic Design and Numerical Analysis of Supersonic Turbine for Turbo Pump
- A Comparison of Hybrid Approaches for Turbofan Engine Gas Path Fault Diagnosis
- Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm
- Taguchi Based Regression Analysis of End-Wall Film Cooling in a Gas Turbine Cascade with Single Row of Holes
- Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime
