EFFECT OF DIFFERENT LIQUID FUELS ON IMPACT PRESSURE OF SUPERSONIC LIQUID FUEL JETS
Published In: INTERNATIONAL CONFERENCE ON ADVANCES IN MECHANICAL, AERONAUTICAL AND PRODUCTION TECHNIQUES
Author(s): ANIRUT MATTHUJAK , PAKORN NGAWKET
Abstract: This study is to measure the impact pressure of supersonic liquid fuel jets injected in quiescent air at various stand-off distances from the nozzle exit. The main focus is to investigate the effect of different liquid fuel jets on the impact pressure. In this study, the supersonic liquid fuel jets are generated by the impact of a projectile, which known as impact driven method, launched by a horizontal single-stage gas gun (HSSGG). The impact pressures of the jets were measured by the PVDF pressure sensor. Moreover, the impact pressures were calculated from the water-hammer equation in order to compare with the measurement. From comparison, the impact pressure of all jets calculated from the equation and the measurement were different. From the measurement, the impact pressures of all jets decrease as the stand-off distance increases. The maximum impact pressure of diesel, kerosene, gasoline and alcohol jets is 662.37, 606.60, 559.50 and 699.5 MPa, respectively. Besides, it was found
- Publication Date: 03-Aug-2014
- DOI: 10.15224/978-1-63248-008-8-109
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TRANSONIC FLOW SIMULATION AROUND THE PLUNGING AIRFOIL WITH OSCILLATION OF FLOW BOUNDARY CONDITION
Published In: INTERNATIONAL CONFERENCE ON ADVANCES IN MECHANICAL, AERONAUTICAL AND PRODUCTION TECHNIQUES
Author(s): A.R. FAGHIHI , M.H DJAVARESHKIAN
Abstract: A new pressure based implicit procedure to solve the Euler and Navier-Stokes equations is developed to predict transonic viscous and inviscid flows around the plunging airfoil with high resolution scheme. In this process, nonorthogonal and non moving mesh with collocated finite volume formulation are used. In order to simulate plunging airfoil, oscillation of flow boundary condition is applied. The boundedness criteria for this procedure are determined from Normalized Variable Diagram (NVD) scheme. The procedure incorporates the eddy-viscosity turbulence model. In the new algorithm, the computation time is considerably reduced. This process is tested for inviscid and turbulent transonic aerodynamic flows around plunging airfoil. The results are compared with other existing numerical solutions and with experiment data. The comparisons show that the resolution quality of the developed algorithm is considerable.
- Publication Date: 03-Aug-2014
- DOI: 10.15224/978-1-63248-008-8-116
- Views: 0
- Downloads: 0