NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
High angle-of-attack aerodynamics of a strake-canard-wing V/STOL fighter configurationHigh angle-of-attack aerodynamic data are analyzed for a strake-canard-wing V/STOL fighter configuration. The configuration represents a twin-engine supersonic V/STOL fighter aircraft which uses four longitudinal thrust-augmenting ejectors to provide vertical lift. The data were obtained in tests of a 9.39 percent scale model of the configuration in the NASA Ames 12-Foot Pressure Wind Tunnel, at a Mach number of 0.2. Trimmed aerodynamic characteristics, longitudinal control power, longitudinal and lateral/directional stability, and effects of alternate strake and canard configurations are analyzed. The configuration could not be trimmed (power-off) above 12 deg angle of attack because of the limited pitch control power and the high degree of longitudinal instability (28 percent) at this Mach number. Aerodynamic center location was found to be controllable by varying strake size and canard location without significantly affecting lift and drag. These configuration variations had relatively little effect on the lateral/directional stability up to 10 deg angle of attack.
Document ID
19840027787
Document Type
Conference Paper
Authors
Durston, D. A. (NASA Ames Research Center Moffett Field, CA, United States)
Schreiner, J. A. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1983
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 83-2510
Distribution Limits
Public
Copyright
Other