Impact of fuselage cross section on the stability of a generic fighter

16th AIAA Applied Aerodynamics Conference

Volumn , Issue , 1998, Pages 515-525

  Hall, Robert M ^a  

^a NASA LANGLEY RESEARCH CENTER   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; STABILITY; VORTEX FLOW;

DATA BASIS; DIRECTIONAL STABILITY; FIGHTER CONFIGURATION; LONGITUDINAL STABILITY; ROLLING MOMENTS;

FUSELAGES;

EID: 84983171275     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.2514/6.1998-2725     Document Type: Conference Paper

References (7)

1. Treiber, David A.; and Muilenburg, Dennis A.: Euler Technology Assessment for Preliminary Aircraft Design Employing OVERFLOW Code With Multiblock Structured-Grid Method. NASA Contractor Report 4651, March 1995.
2. Finley, Dennis B.; and Karman, Steve L., Jr.: Euler Technology Assessment for Preliminary Aircraft Design-Compressibility Predictions by Employing the Cartesian Unstructured Grid SPLITFLOW Code. NASA Contractor Report 4710, March 1996.
3. Kinard, Tom A.; and Raj, Pradeep: Euler Technology Assessment for Preliminary Aircraft Design-Compressibility Predictions by Employing the Unstructured Grid USM3D Code. NASA Contractor Report 4711, March 1996.
4. Rao, Dhanvada M.; and Bhat, M. K.: Subsonic Investigations of Vortex Interaction Control for Enhanced High-Alpha Aerodynamics of a Chine Forebody/Delta Wing Configuration. NASA Contractor Report 189641, June 1992.
5. Rao, Dhanvada M.; and Bhat, M. K.: High-Alpha Vortex Decoupling Investigations on a Chine Forebody/Delta Wing Configuration at Transonic Mach Numbers. NASA Contractor Report 189642, June 1992.
6. Penaranda, Frank E.; and Freda, M. Shannon: Aeronautical Facilities Catalogue. Volume I-Wind Tunnels. NASA RP-1132, 1985.
7. Nutter, J.: Leading-Edge Separation from a Thick, Conical, Slender Wing at Small Angles of Incidence. Journal of Engineering Mathematics, Vol. 15, April 1981, pp. 103-117.