Missile Vortex Wake Measurements.
Final rept. 1 Mar 77-30 Jun 78,
TENNESSEE UNIV SPACE INST TULLAHOMA
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This report describes the preliminary results obtained using a dual scatter, moving fringe laser velocimeter system to measure the velocity field downstream of a missile body at high angles of attack. The measurements were made in the NASAMarshall Space Flight Center Bisonic Wind Tunnel. Problems associated with excessive amounts of oil in the flow prevented a complete characterization of the flow field. Two components of velocity were measured in two planes downstream of the missile nose at an angle of attack of 19.5 deg. The mean velocity, turbulent intensity and kurtosis of the probability density distribution were determined at 45 spatial locations. The mean flow velocity of the wind tunnel freestream was found to oscillate about the mean flow with a time period between 3 and 4 seconds. The mean horizontal velocity component did not vary appreciably less than 1 ftsec out of 300 ftsec, but the vertical component of velocity exhibited both positive and negative components in the vortex flow. Velocity histograms and modal velocities were determined at each spatial location. The report describes the UTSI laser velocimeter system and makes recommendations for its future use in characterizing the missile vortex flows. Author
- Test Facilities, Equipment and Methods
- Guided Missiles
- Fluid Mechanics