Pressure coefficient evaluation on the surface of the SONDA III model tested in the TTP Pilot Transonic Wind Tunnel

2014 Joint IMEKO TC1-TC7-TC13 Symposium: Measurement Science Behind Safety and Security

Reis, M.L.C.C.^1 ; Falcao Filho, J.B.P.^1 ; Basso, E.^1 ; Caldas, V.R.^2

Institute of Aeronautics and Space Pr. Mal. Eduardo Gomes, 50, São José dos Campos, SP

CEP 12228904, Brazil^1

University of Taubate, Av. 9 de Julho, 199, Taubate, SP

CEP 12020-200, Brazil^2

关键词: Aerodynamic phenomena;    Computational fluid dynamics simulations;    Estimated parameter;    Measured parameters;    Pressure coefficients;    Propagation of uncertainties;    Transonic wind tunnels;    Uncertainty evaluation;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/588/1/012003/pdf
DOI  :  10.1088/1742-6596/588/1/012003

来源: IOP

【 摘 要 】

A test campaign of the Brazilian sounding rocket Sonda III was carried out at the Pilot Transonic Wind Tunnel, TTP. The aim of the campaign was to investigate aerodynamic phenomena taking place at the connection region of the first and second stages. Shock and expansion waves are expected at this location causing high gradients in airflow properties around the vehicle. Pressure taps located on the surface of a Sonda III half model measure local static pressures. Other measured parameters were freestream static and total pressures of the airflow. Estimated parameters were pressure coefficients and Mach numbers. Uncertainties associated with the estimated parameters were calculated by employing the Law of Propagation of Uncertainty and the Monte Carlo method. It was found that both uncertainty evaluation methods resulted in similar values. A Computational Fluid Dynamics simulation code was elaborated to help understand the changes in the flow field properties caused by the disturbances.