Accession Number:

AD0734236

Title:

Four Prop Tilt Wing with Cyclic Pitch Propellers: Results of Full Span Wind Tunnel Test/Phase 2

Descriptive Note:

Contractor test rept.

Corporate Author:

BOEING VERTOL CO PHILADELPHIA PA

Personal Author(s):

Report Date:

1971-06-01

Pagination or Media Count:

301.0

Abstract:

The report presents the results of wind tunnel test BVWT 067, the Phase II test of a two phase test program, performed in the Boeing-Vertol V STOL wind tunnel on a powered four prop tilt wing full span model equipped with cyclic pitch propellers for longitudinal control. Items evaluated through transitional flight, include cyclic pitch effectiveness, descent performance with cyclic pitch inputs, the effect of cyclic on longitudinal and lateral directional stability plus the influence of cyclic action on the effectiveness of the aircraft surface controls stabilizer for longitudinal trim and differentially deflected flapsspoiler for rollyaw control. An in-ground effect investigation with a moving ground plane was also conducted to establish the influence of the ground on cyclic pitch effectiveness and on stability characteristics with cyclic pitch inputs.

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE