Experimental investigation of a new device to control the asymmetric flowfield on forebodies at large angles of attack
© 1990 American Institute of Aeronautics and Astronautics, Inc. All rights reserved. An exploratory experimental investigation of a new device to control the asymmetric flowfield on forebodies at large angles of attack has been conducted. The device is a rotatable forebody tip, which varies in cross section from circular at its base to elliptic at its tip. The device itself extends over a small portion of the aircraft or missile forebody. The device provides two important improvements. First, it replaced the normally random behavior of the nose side force as a function of nose tip orientation with a predictable and generally sinusoidal distribution and, second, the device showed promise for use as pat of a vehicle control system, to be deflected in a prescribed manner to provide additional directional conuol for the vehicle. The device was tested on a cone/cylinder model having a 10 deg semi-apex angle and on a 3.0 caliber tangent ogive model, each with a base diameter of 3.5 in, for angles of attack from 30 to 60 deg. Data were taken from 3 circumferential rows of pressure taps on each model at a Reynolds number of 84,000 based on cylinder diameter and by a helium-bubble flow visualization technique at a Reynolds number of 24,000.
Moskovitz, CA; Hall, RM; Dcjarncttct, FR
28th Aerospace Sciences Meeting, 1990
Digital Object Identifier (DOI)