Tabulated Data from a Pressure-distribution Investigation at Mach Number 2.01 of the Wing of a Canard Airplane ModelCornelius. Driver1959
Effect of Forebody Strakes on the Aerodynamic Characteristics in Pitch and Sideslip of a Hypersonic Airplane Configuration at Mach Numbers of 1.41, 2.01, and 6.86Cornelius. Driver1959
Effects of Wing Height on the Stability and Control Characteristics at a Mach Number of 2.01 of a Canard Airplane Configuration with a 70° Delta WingCornelius. Driver1960
Static Stability and Control Characteristics of an Airplane Model with Tail Surfaces Outboard of the Wing Tips at a Mach Number of 2.01Cornelius. Driver1959
Stability and Control Characteristics at a Mach Number of 2.01 of a Supersonic VTOL Airplane Model Having a Broad Fuselage and Small Delta WingsCornelius. Driver1961