Experimental Performance of a Ventral Nozzle With Pitch and Yaw Vectoring Capability for Sstovl Aircraft

Document Number: 931412

Date Published: April 1993

Author(s):
Barbara S. Esker - NASA Lewis Research Center
Jack G. McArdle - NASA Lewis Research Center

Abstract:
Aircraft with supersonic, short takeoff and vertical landing capability have been proposed to replace some of the current high-performance aircraft. Several of these configurations use a ventral nozzle in the lower fuselage, aft of the center of gravity, for lift or pitch control. Internal vanes canted at 20\mD were added to a swivel-type ventral nozzle and tested at tailpipe-to-ambient pressure ratios up to 5.0 on the powered lift facility at NASA Lewis Research Center. The addition of sets of four or seven vanes decreased the discharge coefficient of the nozzle by at least 6 percent or more of the vertical force. In addition, this side force caused only a small loss in vertical force in comparison to the nozzle without vanes. The net thrust force was 8\mD from the vertical for four vanes and 10.5\mD for seven.

File Size: 1436K
Product Status: In Stock

See other papers presented at Aerospace Atlantic Conference & Exposition, April 1993, Dayton, OH, USA, Session: Aerospace Atlantic Conference & Exposition

Purchase more technical papers and save! With TechSelect, you decide what SAE Technical Papers you need, when you need them, and how much you want to pay. Learn more >