Accession Number:

AD0734235

Title:

Four Prop Tilt Wing with Cyclic Pitch Propellers: Results of Full Span Wind Tunnel Test/Phase 1

Descriptive Note:

Contractor test rept. May-Jul 1970

Corporate Author:

BOEING VERTOL CO PHILADELPHIA PA

Report Date:

1970-10-01

Pagination or Media Count:

252.0

Abstract:

The report presents the results of wind tunnel test BVWT 061 Phase I test of two phase test program performed in the Boeing-Vertol VSTOL wind tunnel on a powered four prop tilt wing full span model equipped with cyclic pitch propellers for longitudinal control. Items evaluated include cyclic pitch control in hover in and out of ground effect, yaw control in performance, plus basic longitudinal stability and control throughout transition with a high horizontal tail. Propeller hub pitching moment and normal force were also measured during this test so that in conjunction with a previous isolated propeller test,the influence of the wingflapsfuselage on the propeller forces and moments could be determined.

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE