NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Prediction of nacelle aerodynamic interference effects at low supersonic Mach numbersThe accuracy of analytical predictions of nacelle aerodynamic interference effects at low supersonic speeds are studied by means of test versus theory comparisons. Comparisons shown include: (1) isolated wing body lift, drag, and pitching moments; (2) isolated nacelle drag and pressure distributions; (3) nacelle interference shock wave patterns and pressure distributions on the wing lower surface; (4) nacelle interference effects on wing body lift, drag, and pitching moments; and (5) total installed nacelle interference effects on lift, drag, and pitching moment. The comparisons also illustrate effects of nacelle location, nacelle spillage, angle of attack, and Mach numbers on the aerodynamic interference. The initial results seem to indicate that the methods can satisfactorily predict lift, drag, pitching moment, and pressure distributions of installed engine nacelles at low supersonic Mach numbers with mass flow ratios from 0.7 to 1.0 for configurations typical of efficient supersonic cruise airplanes.
Document ID
19810009465
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kulfan, R. M. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1980
Publication Information
Publication: NASA. Langley Res. Center Supersonic Cruise Res. 1979, Pt. 1
Subject Category
Aerodynamics
Accession Number
81N17988
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitle19810009458Collected WorksSupersonic Cruise Research 1979, part 1
No Preview Available