Accession Number:

AD0608304

Title:

STATIC AERODYNAMIC CHARACTERISTICS AT MACH 5 AND 8 OF AN AERODYNAMICALLY CONTROLLABLE WINGED RE-ENTRY CONFIGURATION; PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS

Descriptive Note:

Technical documentary rept.

Corporate Author:

GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY

Personal Author(s):

Report Date:

1963-09-01

Pagination or Media Count:

157.0

Abstract:

Six-component aerodynamic data were obtained at Mach 5 and 8 for a winged re-entry configuration having aerodynamic controls. The basic model consisted of a clipped delta wing with an over-slung body. The main controls tested were a deflected apex and partial-span trailing-edge flaps. Data were also obtained on the effect of tip fins, full-span trailing-edge flap, and trailing-edge spoiler. At Mach number 5 the data were obtained over an angle of attack range from -30 degrees to 45 degrees at a unit Reynolds number of 2.26 x 10 to the 6th power. At Mach number 8 the angle of attack range was -54 degrees to 54 degrees at the same unit Reynolds number.

Subject Categories:

  • Guided Missile Reentry Vehicles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE