Add to ORKGReport presenting an investigation of the separate and combined effects of twist and camber, fences, and horizontal-tail height on the static longitudinal stability of a 45 degree sweptback wing-fuselage combination of aspect ratio 8 at Mach number 0.19. Two different wings were investigated, one untwisted and one with twist and cambered. Results regarding wing-fuselage configuration and wing-fuselage configurations with horizontal tail are provided
Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were t...
Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal...
Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of thr...
Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...
Contains low-speed longitudinal stability characteristics of a 52 degree sweptback wing of aspect ra...
Results are presented of tests conducted in the Langley stability tunnel to determine the effects of...
Report presents the results of an investigation conducted in the Langley stability tunnel to determi...
The static lateral- and directional-stability characteristics of a high-speed fighter-type airplane,...
"Experimental results showing the static longitudinal-stability and control characteristics of a mod...
"December 19, 1952."Includes bibliographical references (p. 23-24).Mode of access: Internet
An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunn...
An investigation was made to determine the effects of vertical-tail size and length and of fuselage ...
An investigation has been made of a complete airplane model having a wing with the quarter-chord lin...
Results of a low-speed wind-tunnel investigation to determine the effect of high-lift devices on the...
Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage...
Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were t...
Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal...
Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of thr...
Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...
Contains low-speed longitudinal stability characteristics of a 52 degree sweptback wing of aspect ra...
Results are presented of tests conducted in the Langley stability tunnel to determine the effects of...
Report presents the results of an investigation conducted in the Langley stability tunnel to determi...
The static lateral- and directional-stability characteristics of a high-speed fighter-type airplane,...
"Experimental results showing the static longitudinal-stability and control characteristics of a mod...
"December 19, 1952."Includes bibliographical references (p. 23-24).Mode of access: Internet
An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunn...
An investigation was made to determine the effects of vertical-tail size and length and of fuselage ...
An investigation has been made of a complete airplane model having a wing with the quarter-chord lin...
Results of a low-speed wind-tunnel investigation to determine the effect of high-lift devices on the...
Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage...
Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were t...
Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal...
Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of thr...