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Wing loads and load distributions throughout the lift range of the Douglas X-3 research airplane at transonic speeds
Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the left wing of the Douglas X-3 to determine the effects of angle of attack and Mach number on the wing characteristics at transonic Mach numbers. The wing had an aspect ratio of 3.09 and a modified 4.5-percent-thick hexagonal section. Data covered a range of lift values and Mach numbers.
Date:
November 9, 1956
Creator:
Keener, Earl R. & Jordan, Gareth H.
System:
The UNT Digital Library
Analysis of the vertical-tail loads measured during a flight investigation of the Douglas X-3 research airplane
From Summary: "Results are presented of an analysis of the strain-gage measurements of vertical-tail loads experienced in rudder pulses, gradually increasing sideslips, and rudder-fixed aileron rolls at transonic speeds with the Douglas X-3 research airplane."
Date:
November 9, 1956
Creator:
Marcy, William L.; Stephenson, Harriet J. & Cooney, Thomas V.
System:
The UNT Digital Library
Dynamic Model Investigation of Two Tail-Sitter Vertically Rising Airplanes to Determine the Altitude Required to Approach Normal Flight Conditions Under Power Failure in Hovering Flight
"An investigation has been undertaken on two dynamic models simulating 1/20-scale and 1/25-scale models of propeller-driven tail-sitter vertically rising airplanes to determine the altitude required to approach normal-flight conditions after power failure in hovering flight. The results of the investigation indicated that, for the two models investigated, an altitude of 3,600 to 5,400 feet may be required to attain normal gliding flight" (p. 1).
Date:
November 9, 1956
Creator:
Klinar, Walter J. & Wilkes, L. Faye
System:
The UNT Digital Library