Compressibility and leading-edge bluntness effects for a 65° delta wing

AIAA Paper

Volumn , Issue , 2004, Pages 8793-8808

  Luckring, J M ^a,b  

^a NASA LANGLEY RESEARCH CENTER   (United States)

^b Building 45   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

MACH NUMBER; PRESSURE COEFFICIENTS; TRANSONIC SPEEDS; VORTEX SEPARATION;

AEROSPACE ENGINEERING; ASPECT RATIO; COMPRESSIBILITY; FLIGHT DYNAMICS; LIFT; REYNOLDS NUMBER; SUBSONIC AERODYNAMICS; SUBSONIC FLOW; TRANSONIC AERODYNAMICS; VORTEX FLOW; WIND TUNNELS;

DELTA WING AIRCRAFT;

EID: 2942715250     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (20)

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3. Smith, J. H. B., "Improved Calculations of Leading-Edge Separation from Slender Delta Wings". RAE TR-66070, 1966.
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10. Luckring, J. M., "Transonic Reynolds Number and Leading-Edge Bluntness Effects on a 65° Delta Wing," AIAA Paper 2003-0753, January 2003.
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13. Chu, J., and Luckring, J. M., "Experimental Surface Pressure Data Obtained on 65° Delta Wing Across Reynolds Number and Mach Number Ranges. Volume 3 - Medium Leading Edge," NASA TM-4645, February 1996.
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