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
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
An investigation was made in the LWAL 7- by 10-foot tunnel of internally balanced, sealed ailerons f...
Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 M...
A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of various modifi...
"In the following, high-speed measurements on a swept-back wing are reported. The curves of lift, mo...
This investigation was carried out for the purpose of determining the effectiveness of ailerons and ...
An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 air...
Ailerons having a beveled trailing edge and a blunt-nose overhang of 35 percent aileron chord on an ...
Wind-tunnel measurements of the pressure distribution were made on a semispan wing tith a modified N...
Analysis indicates that this use of spoiler ailerons is feasible and desirable for normal emergency ...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
An investigation was made in the LWAL 7- by 10-foot tunnel of internally balanced, sealed ailerons f...
Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 M...
A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of various modifi...
"In the following, high-speed measurements on a swept-back wing are reported. The curves of lift, mo...
This investigation was carried out for the purpose of determining the effectiveness of ailerons and ...
An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 air...
Ailerons having a beveled trailing edge and a blunt-nose overhang of 35 percent aileron chord on an ...
Wind-tunnel measurements of the pressure distribution were made on a semispan wing tith a modified N...
Analysis indicates that this use of spoiler ailerons is feasible and desirable for normal emergency ...
An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1....
An investigation was made in the LWAL 7- by 10-foot tunnel of internally balanced, sealed ailerons f...
Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 M...