NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Transonic Investigation of Aerodynamic Characteristics of a Swept-Wing Fighter-Airplane Model with Leading-Edge Droop in Combination with Outboard Chord-Extensions and NotchesAn investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 60 and 20 degrees chord-extension overhangs of 0.075c and 0.15c (where c inboard end of the 0.075c chord-extension to depths of 0.075c and 0.l25c, and indention of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included. Generally, the model wing modifications provided only slight improvements of the airplane longitudinal stability characteristics, but did substantially reduce the airplane drag coefficients at moderate and high lifting conditions.
Document ID
20040027948
Acquisition Source
Langley Research Center
Document Type
Other - NASA Technical Note (TN)
Authors
Whitcomb, Charles F.
(NASA Langley Research Center Hampton, VA, United States)
Norton, Harry T., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
May 1, 1961
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
L-1060
NASA-TN-D-834
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available