Add to ORKGThe variation of the intensity of buffeting experienced throughout the operational region of the semitailless Northrop X-4 airplane and the values of maximum and peak normal-force coefficients in the Mach number range from 0.42 to 0.92 have been determined. The results are compared with data obtained with the swept-wing Douglas D-558-II airplane
Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data...
A series of calculations of the dynamic response of airplane wings to gusts were made with the purpo...
Two rocket-powered models representative of a fighter-type airplane were investigated in flight at M...
The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane...
The buffeting loads measured on the wing and tail of a fighter airplane during 194 maneuvers are giv...
Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bendin...
The buffeting loads measured on the wing and tail of a fighter-type airplane during 194 manuevers ar...
Three rocket-propelled buffet-research models have been flight tested to determine the buffeting cha...
Flight tests were conducted on a North American P-51D airplane to establish the maximum lift coeffic...
A brief investigation was made of the longitudinal-stability characteristics of a YF-84A airplane (A...
Tests were made in the Langley 7- by 10-foot tunnel on a 0.182-scale model of an F4U-1 airplane with...
An investigation has been made to determine the effect of wing fences, a wing leading-edge extension...
An investigation was made by the NACA wing-flow method to determine the drag, pitching-moment, lift,...
An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 air...
An investigation of the air-stream fluctuations at the tail of the D-558-1 airplane has been made at...
Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data...
A series of calculations of the dynamic response of airplane wings to gusts were made with the purpo...
Two rocket-powered models representative of a fighter-type airplane were investigated in flight at M...
The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane...
The buffeting loads measured on the wing and tail of a fighter airplane during 194 maneuvers are giv...
Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bendin...
The buffeting loads measured on the wing and tail of a fighter-type airplane during 194 manuevers ar...
Three rocket-propelled buffet-research models have been flight tested to determine the buffeting cha...
Flight tests were conducted on a North American P-51D airplane to establish the maximum lift coeffic...
A brief investigation was made of the longitudinal-stability characteristics of a YF-84A airplane (A...
Tests were made in the Langley 7- by 10-foot tunnel on a 0.182-scale model of an F4U-1 airplane with...
An investigation has been made to determine the effect of wing fences, a wing leading-edge extension...
An investigation was made by the NACA wing-flow method to determine the drag, pitching-moment, lift,...
An investigation of the characteristics of a wing with an aspect ratio of 9.0 and an NACA 65-210 air...
An investigation of the air-stream fluctuations at the tail of the D-558-1 airplane has been made at...
Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data...
A series of calculations of the dynamic response of airplane wings to gusts were made with the purpo...
Two rocket-powered models representative of a fighter-type airplane were investigated in flight at M...