Accession Number:

ADP002271

Title:

Augmentation of Fighter-Aircraft Performance by Spanwise Blowing over the Wing Leading Edge,

Personal Author(s):

• Seginer,A.
• Salomon,M.

Corporate Author:

NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER

Report Date:

1983-07-01

Abstract:

Spanwise blowing over the wing canard of a 135 model of a close-coupled-canard fighter-airplane configuration similar to the Kfir-C2 was investigated experimentally in low-speed flow. Tests were conducted at airspeeds of 30 msec Reynolds number of 180000 based on mean aerodynamic chord with angle-of-attack sweeps form -8 deg to 60 deg, and yaw-angle sweeps from -8 deg to 36 deg at fixed angles of attack 0 deg, 10 deg, 20 deg, 25 deg, 30 deg, and 35 deg. Significant improvement in lift-curve slope, maximum lift, drag polar and laterallimit. In spite of the highly swept 60 deg leading edge, the efficiency of the lift augmentation by blowing was relatively high and was found to increase with increasing blowing momentum on the close-coupled-canard configuration. Interesting possibilities of obtaining much higher efficiencies with swirling jets were indicated. Author

Supplementary Note:

This article is from 'Aerodynamics of Vortical Type Flows in Three Dimensions: Conference Proceedings Held at Rotterdam, Netherlands on 25-28 April 1983,' AD-A135 157, p33-1-33-26.

Pages:

0026

Descriptors:

• *FLOW FIELDS
• *SWEPT WINGS
• CANARD CONFIGURATIONS
• LEADING EDGES
• FIGHTER AIRCRAFT
• FLIGHT ENVELOPE
• AUGMENTATION
• LIFT TO DRAG RATIO
• ANGLE OF ATTACK
• SUBSONIC FLOW

Identifiers:

• Component reports

Subject Categories:

Communities Of Interest:

• Air Platforms

File Size:

0.00MB