| Jurnal Angkasa Tahun 2010 Oleh Vicky Kurnia Sari Mohammad Ardi Cahyono |
ANALISIS KARAKTERISTIK AERODINAMIKA PADA MODEL NOSE ROKET KECEPATAN SUPERSONIK DENGAN SIMULASI COMPUTATIONAL FLUID DYNAMICS-FLUENT |
| ABSTRAK |
| An aerodynamic characteristic is a very important thing in the field of aerodynamics applications intended to obtain the aerodynamics’s shape. The research done on the nose of rocket, Tangent Ogive Type at supersonic speed uses simulation of computational fluids dynamics – CFD (Fluent) with determination of air flow conditions that occur on the surface of the rocket nose for get a shock wave. The purpose of simulation is to find characteristics of air flow conditions on rocket nose when shock wave occur through analysis of shock wave visualization of contour mach number, temperature, pressure and air density and teoritically calculation of shock wave angle, pressure, mach number, temperature and air density of air flow in the rear shock wave from variation mach number between 1 – 5 Mach and flow condition on altitude of 10 km or 32,808 ft, at temperature of 232.252 Kelvin and pressure 26,501 Pa (Standard Atmosphere), that know the higher velocity flow hence the smaller the shock wave angle, pressure, temperature and air density increase in the rear shock wave. Keywords: Aerodynamics, Nose, Supersonic, Shock Wave, Tangent Ogive, CFD |
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