Accession Number:

AD0636750

Title:

A PRELIMINARY INVESTIGATION TO STUDY THE EFFECT OF FLAT SPOILERS ON THE AERODYNAMIC CHARACTERISTICS OF WINGS AT ANGLES OF ATTACK FROM 0 DEGREES TO 90 DEGREES.

Descriptive Note:

Research and development rept.

Corporate Author:

DAVID TAYLOR MODEL BASIN WASHINGTON D C AERODYNAMICS LAB

Personal Author(s):

Report Date:

1966-04-01

Pagination or Media Count:

34.0

Abstract:

Flat spoilers were tested on a semispan wing as a possible leading-edge, upper-surface device for controlling flow separation on wings rotated through 90 degrees for application to tilt-wing VSTOL aircraft. Model tests indicated that a spoiler height of 0.10 wing chord at the 0.15 wing chord location was capable of partially controlling flow separation. Author

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE