2 Matching Results
Results open in a new window/tab.
Results:
1 - 2 of
2
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Longitudinal Stability and Control Characteristics at a Mach Number of 1.40
Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic tunnel to determine the longitudinal stability and control characteristics of a model of a supersonic airplane configuration at Mach number 1.40. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results indicated a high degree of longitudinal stability that was fairly constant throughout the trim-lift-coefficient range.
Date:
April 3, 1950
Creator:
Spearman, M. Leroy
System:
The UNT Digital Library
Wing-flow measurements of longitudinal stability and control characteristics of a supersonic airplane configuration having a 42.8 degree sweptback circular arc wing with aspect ratio 4.0, taper ratio 0.50, and sweptback tail surfaces
Report presenting the results of an investigation at transonic speeds by the wing-flow method of the longitudinal stability characteristics of a 42.8 degree sweptback supersonic airplane configuration. Lift, pitching-moment, and rolling-moment characteristics of the semispan model as well as stabilizer hinge moments and effective downwash at the tail were measured over a range of Mach numbers. The wing-flow data is compared to data for the same configuration from other research facilities.
Date:
April 3, 1950
Creator:
Crane, Harold L. & Adams, James J.
System:
The UNT Digital Library