Transonic Experimental Observations of Abrupt Wing Stall on an F/A-18E Model

• Published in: Journal of aircraft 2005-05, Vol.42 (3), p.586-599
• Main Authors: McMillin, S. Naomi, Hall, Robert M, Lamar, John E
• Format: Article
• Language: English
• Subjects: Aerodynamics; Aircraft; Flow velocity; Physics; Wind tunnels
• ISSN: 0021-8669; 1533-3868
• DOI: 10.2514/1.3152

A transonic wind tunnel test of an 8% F/A 18E model was conducted in the NASA Langley Research Center 16 ft Transonic Tunnel to investigate on surface flow physics during stall. The technical approach employed focused on correlating static (or time averaged) and unsteady wind tunnel test data to the unsteady wing stall events using force, moment, pressure, and pressure sensitive paint measurements. This paper focuses on data obtained on the preproduction configuration of the F/A 18E aircraft at Mach number of 0.90. The flow unsteadiness occurring on the wing as the wing went through the stall process was captured using the time histories of balance and pressure measurements and by calculating the root mean square (rms) for a number of instrument signals. The second step was to gather global perspectives on the pressures influencing the wing stall process. The abrupt wing stall experienced by the 8% F/A 18E model was observed to be an unsteady event triggered by the rapid advancement of separation, which had migrated forward from the trailing edge, to the leading edge flap hingeline over a very small increment in angle of attack. The angle of attack at which this stall occurred varied, from run to run, over a 1 deg increment. The abrupt wing stall was observed, using pressure sensitive paint, to occur simultaneously on both wing panels or asymmetrically. The pressure sensitive paint data and wing root bending moment data were essential in providing insight to the flow structures occurring over the wing and the possible asymmetry of those flow structures. A repeatability analysis conducted on eight runs of static data provided a quick and inexpensive examination of the unsteady aerodynamic characteristics of abrupt wing stall. The results of the repeatability analysis agreed extremely well with data obtained using unsteady measurement techniques. This approach could be used to identify test conditions for more complex unsteady data measurements using special instrumentation.[PUBLICATION ABSTRACT]