Add to ORKGA three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression shock and extended to higher Mach numbers the speeds at which such changes occurred
The effect of spsnwise aileron location on the rolling effective-ness of 0.2-chord plain faired aile...
This report is the fourth of a series on systematic tests conducted which compares lateral control d...
A 0.10-scale model of a swept-wing fighter airplane was tested in the Langley high-speed 7- by 10-fo...
A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees...
Three model wings, two with typical slotted ailerons and one with typical frise ailerons, have been ...
An analysis of the principal results of recent control-surface research pertinent to transonic fligh...
An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper...
This report covers the sixth of a series of investigations in which various lateral control devices ...
An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ail...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
' s u " m Y A n investigation at subscwic and transonic speeds has been performsd in the L...
Tests showed the effect of the ailerons and the tip shapes on the general performance of the wing, a...
Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings ...
Tests were made with ordinary flap-type ailerons on two wings with different amounts of taper, one m...
Results are presented of wind-tunnel tests made at low speed of various small-scale models of sweptb...
The effect of spsnwise aileron location on the rolling effective-ness of 0.2-chord plain faired aile...
This report is the fourth of a series on systematic tests conducted which compares lateral control d...
A 0.10-scale model of a swept-wing fighter airplane was tested in the Langley high-speed 7- by 10-fo...
A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees...
Three model wings, two with typical slotted ailerons and one with typical frise ailerons, have been ...
An analysis of the principal results of recent control-surface research pertinent to transonic fligh...
An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper...
This report covers the sixth of a series of investigations in which various lateral control devices ...
An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ail...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
' s u " m Y A n investigation at subscwic and transonic speeds has been performsd in the L...
Tests showed the effect of the ailerons and the tip shapes on the general performance of the wing, a...
Measured values of lift, drag, and pitching moment at M(sub o) = 1.53 are presented for seven wings ...
Tests were made with ordinary flap-type ailerons on two wings with different amounts of taper, one m...
Results are presented of wind-tunnel tests made at low speed of various small-scale models of sweptb...
The effect of spsnwise aileron location on the rolling effective-ness of 0.2-chord plain faired aile...
This report is the fourth of a series on systematic tests conducted which compares lateral control d...
A 0.10-scale model of a swept-wing fighter airplane was tested in the Langley high-speed 7- by 10-fo...