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) : Brasseur, Gary W.

Report Date : APR 1966

Pagination or Media Count : 34

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 V/STOL 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)

Descriptors :   (*SPOILERS, *TILT WINGS), (*AERODYNAMIC CHARACTERISTICS, TILT WINGS), (*CONVERTIBLE PLANES, STABILITY), ANGLE OF ATTACK, MODEL TESTS

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE