Transonic experimental observations of abrupt wing stall on an F/A-18E model

Journal of Aircraft

Volumn 42, Issue 3, 2005, Pages 586-599

  McMillin, S Naomi ^a,b   Hall, Robert M ^a,b   Lamar, John E ^a,b  

^a NASA LANGLEY RESEARCH CENTER   (United States)

^b Distinguished Research Associate   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; AIRCRAFT; CORRELATION METHODS; DATABASE SYSTEMS; MATHEMATICAL MODELS; PRESSURE EFFECTS;

ABRUPT WING; DATA MEASUREMENTS; TRANSONIC TUNNEL; WING-ROOT BENDING-MOMENT DATA;

WIND TUNNELS;

EID: 22544478837     PISSN: 00218669     EISSN: 15333868     Source Type: Journal    
DOI: 10.2514/1.3152     Document Type: Article

References (4)

1. Hall, R., and Woodson, S., "Introduction to the Abrupt Wing Stall (AWS) Program," Journal of Aircraft, Vol. 41, No. 3, 2004, pp. 425-435.
2. Capone, F. J., Bangert, L. S., Asbury, S. C., Mills, C. T. L., and Bare, E. A., "The NASA Langley 16 Foot Transonic Tunnel - Historical Overview, Facility Description, Calibration, Flow Characteristics, and Test Capabilities," NASA TP 3521, Oct. 1995.
3. Schuster, David M., and Byrd, James E., "Transonic Unsteady Aerodynamics of the F/A-18E at Conditions Promoting Abrupt Wing Stall," Journal of Aircraft, Vol. 41, No. 3, 2004, pp. 485-492.
4. Sprinkle, D. R., Obara, C. J., Amer, T. R., Leighty, B. D., Carmine, M. T., Burkett, C. G., and Sealey, B. S., "Langley 16-Ft. Transonic Tunnel Pressure Sensitive Paint System," NASA TM-2001-211017, June 2001.