Accession Number:

AD0647386

Title:

WIND TUNNEL TEST REPORT, LIFT FAN POWERED SCALE MODEL

Descriptive Note:

Corporate Author:

GENERAL ELECTRIC CO CINCINNATI OH ADVANCED ENGINE AND TECHNOLOGY DEPT

Personal Author(s):

Report Date:

1963-11-01

Pagination or Media Count:

175.0

Abstract:

Data were obtained to define the static characteristics in and out of ground effect aerodynamic characteristics in forward flight for the transition, conversion, and low speed conventional flight modes and flight characteristics at low translational speeds near hovering in vertical, lateral, and rearward directions. In addition, wing surface static pressures and wing fan inlet closure door hinge moments were measured. The data indicate an adverse ground effect on static lift at heights less than 2 wing fan diameters with a reduction of approximately 6 at 1.0 diameter. A corresponding reduction in fan power at constant fan RPM compensates for the lift reduction if operation at constant power is considered. The effects of wing fan and nose fan operation are destabilizing with respect to angle of attack. Nose fan operation is slightly destabilizing in yaw, but the data indicate positive lateral-directional stability for the entire range of thrust coefficient in fan-powered flight. A favorable ground effect on lift is obtained with increasing forward speed as would occur during short take-off operation, with an increase of approximately 22 above the out-of-ground effect lift at a thrust coefficient of .885. The data obtained in ground effect were uncorrected for wall effects but this correction is believed to be small compared with the lift increase shown.

Subject Categories:

  • VSTOL
  • Research and Experimental Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE