This report presents the results of a wind tunnel test performed in the Boeing-Vertol wind tunnel on a 1/3 scale V/STOL 4-bladed cyclic pitch propeller # having a total Activity Factor of 640. The propeller was tested as both an isolated propeller and as an installed propeller. The primary objectives of the test were to determines (1) the effectiveness of cyclic pitch control for longitudinal control during hover and transition, (2) the change in power required for cyclic pitch control and (3) blade and hub loads for use in design and for verification of analytical methods.
In 1980 NASA Langley Research Center and the Federal Aviation Administration began an extensive research and development program to quantitatively assess transport airplane crashes. As part of this program, a survivable, full-scale crash test of a transport airplane was planned. On December 1,1984, the FAA, NASA and industry contractors conducted a remotely piloted crash test using an out-of-service Boeing 720 jet transport airplane. A major purpose of the test, designated the Controlled Impact Demonstration is to advance analytical modeling techniques for simulating transport crash dynamics. This paper describes NASA analyses using the nonlinear finite-element computer code Dynamic Crash Analysis of Structures. The research is described beginning with transport fuselage section drop tests and single frame models, culminating with finite-element models of the Boeing 720 airplane. The final model based on test and analysis, simulates the Controlled Impact Demonstration impact with excellent correlation.
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