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Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane

Description: Memorandum presenting an investigation of the steady-state wing loads conducted on a Boeing B-52 airplane over a range of Mach numbers and altitudes. Results regarding flight tests and air-load calculations are provided.
Date: April 23, 1958
Creator: Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Loads experienced in flights of two swept-wing research airplanes in the angle-of-attack range of reduced stability

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Elevon Hinge Moments on the XF-92A Delta-Wing Airplane

Description: Report presenting flight measurements of the elevon hinge moments on the Convair XF-92A delta-wing airplane over a range of Mach numbers during longitudinal elevon pulses, aileron rolls, and wind-up turns. During wind-up turns, the hinge moments become nonlinear at about the angle of attack at which the airplane experiences a marked decrease in longitudinal stability.
Date: January 13, 1955
Creator: Johnson, Clinton T. & Kuhl, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight measurements of wing loads on the Convair XF-92A delta-wing airplane

Description: Report presenting a flight investigation at a range of altitudes to determine the wing loads on the Convair XF-92A airplane over the lift range of the airplane at subsonic and transonic speeds. Theoretical lift-curve slope for a delta wing was calculated and compared with the flight data at a Mach number of 0.75.
Date: May 25, 1955
Creator: Kuhl, Albert E. & Johnson, Clinton T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of flight-determined and predicted effects of flexibility on the steady-state wing loads of the B-52 airplane

Description: From Introduction: "This paper presents the results obtained during the phase of the B-52 flight investigation concerned with the steady-state wing loads. Where possible, the effects of Mach number and flexibility on the measured load are analyzed and presented."
Date: April 23, 1958
Creator: Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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