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Loads experienced in flights of two swept-wing research airplanes in the angle-of-attack range of reduced stability
Report presenting load measurements using the swept-wing Bell X-5 and Douglas D-558-II research airplanes during flights in which reductions of longitudinal stability were experienced when pilots attempted to perform routine test maneuvers at moderate values of lift. Results regarding the maximum angles of attack and sideslip measured, pitching accelerations, horizontal-tail loads, wing loads, and stability deficiencies are provided.
Date:
June 5, 1953
Creator:
Robinson, Glenn H.; Drake, Hubert M. & Kuhl, Albert E.
System:
The UNT Digital Library
Low-speed, large-scale investigation of aerodynamic characteristics of a semispan 49 degree sweptback wing with a Fowler flap in combination with a plain flap, slats, and fences
Report presenting an investigation in the full-scale tunnel to determine the effects of a Fowler type slotted flap on the aerodynamic characteristics of a semispan 49.1 degree sweptback wing with NACA 65A006 airfoil sections streamwise, an aspect ratio of 3.78, and a taper ratio of 0.59. Results regarding the pitching-moment curve, effect of flap deflection, and lift increments are provided.
Date:
June 5, 1953
Creator:
Whittle, Edward F., Jr. & Lipson, Stanley
System:
The UNT Digital Library
The effects of nacelles and of extended split flaps on the longitudinal characteristics of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and an aspect ratio of 10
Report presenting an investigation to evaluate the effects of nacelles and extended split flaps on the longitudinal characteristics of a wing-fuselage-tail combination of a type believed to be suitable for long-range high-speed airplanes. Wind tunnel tests to study the effects of the nacelles and flaps were conducted at a range of Mach and Reynolds numbers. Results regarding the effects of the nacelles with the tail off, effects of tail height, effects of nacelles with the tail on, and effects of flaps are provided.
Date:
June 5, 1953
Creator:
Tinling, Bruce E. & Lopez, Armando E.
System:
The UNT Digital Library
Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees
From Introduction: "The airfoil sections tested, which differ only in thickness ratio, were the NACA 64-006, 64-008, 64-010, and 641-012. Lift, drag, and pitching-moment data were obtained for Mach numbers of 0.3 to that for tunnel choke at angles of attack of -2^o to 31^o. The results of this investigation are reported herein."
Date:
June 5, 1953
Creator:
Wilson, Homer B., Jr. & Horton, Elmer A.
System:
The UNT Digital Library
Gust-Tunnel Investigation to Determine Effects of Center-of-Gravity Position on the Gust Loads of a Delta-Wing Model With Leading Edge Swept Back 60 Degrees
Report presenting an investigation to determine the effects of center-of-gravity position on the gust loads of a delta-wing model with the leading edge swept back 60 degrees. A 15-percent change in the center-of-gravity position on the mean geometric chord produced a 7.5-percent change in load for the model in a sharp-edge gust and a 35-percent change in load in a gust with a 6.5 chord gradient distance.
Date:
June 5, 1953
Creator:
Reisert, Thomas D. & Maglieri, Domenic J.
System:
The UNT Digital Library