Add to ORKGResults are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of attack of -2 degrees to about 24 degrees to determine the lateral control characteristics of spoilers with various wing chord-wise and spanwise locations and spoiler spans and deflections on thin 60 degree delta wing of NACA 65a003 airfoil section parallel to free stream
Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of at...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of modifications ...
In this report are presented the results of wind-tunnel tests of retractable spoilers on the upper s...
Wind tunnel tests of swept-wing fighter aircraft with spoiler-slot-deflector lateral control system
This report presents the results of flight tests made to determine the lateral control characteristi...
An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach number...
Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of at...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of modifications ...
In this report are presented the results of wind-tunnel tests of retractable spoilers on the upper s...
Wind tunnel tests of swept-wing fighter aircraft with spoiler-slot-deflector lateral control system
This report presents the results of flight tests made to determine the lateral control characteristi...
An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach number...
Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of at...
Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar...
Report presenting an investigation in the 7- by 10-foot wind tunnel of the effects of modifications ...