Low speed flow angularity results are presented showing flow direction at the nacelle locations on the Boeing 727-200. Flow angle probes (yawheads) were used for measurements at side and center inlet positions on the aft fuselage. A range of flap settings were tested with flap angles of 0 deg, 15 deg, and 40 deg selected for investigation. (Author)
Low Speed Wind Tunnel Flow Field Results for Jt8d Refan Engines on the Boeing 727-200
1974
25 pages
Report
Keine Angabe
Englisch