EXPERIMENTAL INVESTIGATION AND COMPUTATIONAL FLUID DYNAMICS ANALYSIS OF MISSILE WITH GRID FIN IN SUBSONIC FLOW

摘要

The present work deals with the investigation of aerodynamic force coefficients and flow field structure in subsonic flow on missile configuration with grid fin using Wind tunnel and CFD. The experimental work has been performed using the low speed wind tunnel, which is having a rectangular test section of 3ft height, 4ft width and 6 ft length. Reynolds number range for the models are Re = 4.79 x 105 to 1.3 x 106 and tested for different angle of attack ranging from 15 to +15. Grid fin usually produce much higher lifting forces and pitching moments to overcome the drag, which are created at high angle of attack operations. CFD is used for the prediction of aerodynamic force coefficients and flow field structure around missile with grid fin is investigated for subsonic flow. The work involves computational analysis using CFD and validating the results using wind tunnel test. The body with grid fin configuration produces the greater normal force coefficient at various angles of attack than planar. The axial force coefficient on the grid fin missile configuration was about 0.8 times greater than planar. The computational results of grid fin from the software package are compared with wind tunnel test data and measured data was observed for missile.