Add to ORKGAn investigation at Mach number 1.92 in the Langley 9-inch supersonic tunnel of a variable body-wing-tail configuration has been made in order to determine and to isolate the aerodynamic effects on each other of the components of the configuration.NACA Research Memorandum L9L28a"March 1, 1950."Title from cover.Includes bibliographical references.An investigation at Mach number 1.92 in the Langley 9-inch supersonic tunnel of a variable body-wing-tail configuration has been made in order to determine and to isolate the aerodynamic effects on each other of the components of the configuration.Mode of access: Internet
Prepared at Langley Research Center."June 1985"--Cover.Includes bibliographical references (p. 66).M...
A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to...
Prepared at Langley Research Center."April 1986"--Cover.Includes bibliographical references (p. 8).M...
"June 14, 1955."Includes bibliographical references (p. 10-11).Mode of access: Internet
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...
An investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.84...
Investigations of the NACA-4-(4)(06)-04 two-blade propeller (design thickness, 0.06 at 0.7-radius st...
All the wings investigated developed at least 90 percent of their steady-state lift in the first 7 c...
An investigation has been conducted at the Langley 4- by 4-foot supersonic pressure tunnel at a Mach...
An investigation was made in the LMAL 7- by 10-foot tunnel of the aerodynamic characteristics of a r...
A program to investigate the aerodynamic characteristics of a family of delta wings with a blunt dou...
The results of tests of 11 triangular wings were conducted at Mach numbers 1.62, 1.92, and 2.40 to d...
An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numb...
An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine th...
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution ...
Prepared at Langley Research Center."June 1985"--Cover.Includes bibliographical references (p. 66).M...
A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to...
Prepared at Langley Research Center."April 1986"--Cover.Includes bibliographical references (p. 8).M...
"June 14, 1955."Includes bibliographical references (p. 10-11).Mode of access: Internet
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...
An investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.84...
Investigations of the NACA-4-(4)(06)-04 two-blade propeller (design thickness, 0.06 at 0.7-radius st...
All the wings investigated developed at least 90 percent of their steady-state lift in the first 7 c...
An investigation has been conducted at the Langley 4- by 4-foot supersonic pressure tunnel at a Mach...
An investigation was made in the LMAL 7- by 10-foot tunnel of the aerodynamic characteristics of a r...
A program to investigate the aerodynamic characteristics of a family of delta wings with a blunt dou...
The results of tests of 11 triangular wings were conducted at Mach numbers 1.62, 1.92, and 2.40 to d...
An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numb...
An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine th...
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution ...
Prepared at Langley Research Center."June 1985"--Cover.Includes bibliographical references (p. 66).M...
A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to...
Prepared at Langley Research Center."April 1986"--Cover.Includes bibliographical references (p. 8).M...