Accession Number:

AD0658330

Title:

LEADING-EDGE SPIKES TO REDUCE THE DRAG OF WINGS AT SUPERSONIC AIRSPEEDS

Descriptive Note:

Corporate Author:

DAVID TAYLOR MODEL BASIN WASHINGTON DC AERODYNAMICS LAB

Personal Author(s):

Report Date:

1957-09-01

Pagination or Media Count:

39.0

Abstract:

A 12-percent-thick section NACA 0012 wing panel with leading-edge spikes was tested at a Mach number of 1.88 to determine whether the wing drag could be reduced in such a manner that the ratio of maximum lift coefficient at landing speed to minimum drag coefficient at high speed would compare favorably with the ratio obtained from a thin, high-speed wing. A 6-percent-thick high- speed wing section NACA 65-006 was tested to provide comparison data for the thick wing. A drag reduction of 20 percent compared to the plain wing was obtained when spikes protruded forward ten times the leading-edge radius. This drag reduction was obtained with a spike spacing of 5 percent of the chord. This drag reduction was not enough to make the ratio of maximum lift coefficient to minimum drag coefficient for the thick wing compare favorably with that for the thin wing.

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE