Shahrood University of Technology Journal of Solid and Fluid Mechanics 2251-9475 13 3 2023 07 23 Investigation of the Effect of Noise Parameters of Jet Using Acoustic Load Calculation Algorithm on the Launch Vehicle During Lift-Off Investigation of the Effect of Noise Parameters of Jet Using Acoustic Load Calculation Algorithm on the Launch Vehicle During Lift-Off 17 27 2914 10.22044/jsfm.2023.12617.3688 FA Mostafa Mahmoodi Assoc. Prof., Aerospace. Eng., Malek Ashtar University, Iran Jamasb Pirkandi Assoc. Prof., Aerospace. Eng., Malek Ashtar University, Iran Davoud Pourabdollah MSc. Student, Mech. Eng., University of Tehran, Tehran, Iran Journal Article 2023 01 24 In this paper, the flow field is investigated by solving the acoustics of the launch vehicle for a specific sample model . During the launch of a space vehicle, the intense sound pressure levels created around the vehicle. Therefor identification and analysis of acoustical loads of launch vehicle is an important issue of consideration. In this study, for calculation of acoustic pressure levels and prediction of noise at the discharge of the nozzle jet, presented formula of Eldred was used with the assistance of MATLAB software and the algorithm and code were obtained to handle acoustical loads. In this research, the geometry of one launch vehicle sample was used. The effective parameters including the slope of deflector and the ratio of nozzle outlet distance from launch pad to the jet outlet diameter, were identified and investigated. The curves of sound pressure levels and contours of SPL around the launch vehicle field are obtained versus to the interval of specified frequencies. In this paper, the flow field is investigated by solving the acoustics of the launch vehicle for a specific sample model . During the launch of a space vehicle, the intense sound pressure levels created around the vehicle. Therefor identification and analysis of acoustical loads of launch vehicle is an important issue of consideration. In this study, for calculation of acoustic pressure levels and prediction of noise at the discharge of the nozzle jet, presented formula of Eldred was used with the assistance of MATLAB software and the algorithm and code were obtained to handle acoustical loads. In this research, the geometry of one launch vehicle sample was used. The effective parameters including the slope of deflector and the ratio of nozzle outlet distance from launch pad to the jet outlet diameter, were identified and investigated. The curves of sound pressure levels and contours of SPL around the launch vehicle field are obtained versus to the interval of specified frequencies. https://jsfm.shahroodut.ac.ir/article_2914_6f5e60cc300629d51b5412d65aaf12e3.pdf