Accession Number:

AD0861041

Title:

Wind Tunnel Tests of a Large-Chord, Swept-Panel Model to Investigate Shock-Induced Separation Phenomena.

Descriptive Note:

Final technical rept. 16 Dec 68-15 Oct 69,

Corporate Author:

LOCKHEED-GEORGIA CO MARIETTA

Personal Author(s):

Report Date:

1969-10-01

Pagination or Media Count:

61.0

Abstract:

The model had a chord of 3.5 feet with a streamwise airfoil section identical to that at 38.9 percent of the semispan of the C-141 wing, but had no taper or twist. Pressure distribution measurements were made through a range of angles of attack and Mach numbers for which data were available on the complete C-141 airplane from previous wind tunnel and flight tests. Fluctuating pressures at several chordwise locations near the shock were measured for a number of test conditions. Author

Subject Categories:

  • Aerodynamics
  • Transport Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE