This is not meant to be a comprehensive presentation of all analysis results, but rather a summary of what has been accomplished and is available to users upon request.

Gulfstream has calculated airflow and particle trajectories around the G-V aircraft using NASA/AMI software (VSAERO and MGAERO). An inviscid (no boundary layer) assumption is invoked for both types of calculations; an additional incompressibility assumption is used for the particle trajectory calculations. Gulfstream has verified with wind tunnel testing that the incompressible assumption is valid up to about Mach 0.70 for the G-V.

Nearly all runs were for a flight profile of 40,000 ft and Mach 0.70. (Initial runs at a higher Mach of 0.77 showed a shock region on top of the fuselage just behind the cockpit area). Airflow and particle data (concentration ratios and concentration factors) are available on a vertical plane through the aircraft fuselage near the center line and on a horizontal plane through the fuselage windows. Data are also available for vertical planes through three wing mounting locations. The wing locations do not include the (not yet finalized) wingpods. Trajectories for three different droplet sizes were run for each location. Results indicate that the bottoms of the wing and fuselage are suitable for sampling of most particle sizes. However, the side and top of the fuselage have significant shadow zones for most droplet sizes and should be used with caution. More details are given starting with Slide 8 of Twohy's Nov 2002 workshop presentation: https://www.eol.ucar.edu/observing_facilities/hiaper-gulfstream-gv.

Other graphical information provided by Gulfstream includes streamlines from the outflow valve on the right-hand side of the aircraft, and boundary layer thickness along the upper and lower fuselage surfaces (the latter for prior results at Mach 0.80).

Link to Studies of HIAPER's Flow Boundary Layer in Progressive Science