Accession Number:

AD0612927

Title:

DATA REPORT FOR LTV LOW SPEED WIND TUNNEL TEST NUMBER 172, TEST OF HIGH MASS RATE VECTORED PROPULSION FLOW MODEL,

Descriptive Note:

Corporate Author:

LING-TEMCO-VOUGHT INC DALLAS TEX LTV VOUGHT AERONAUTICS DIV

Personal Author(s):

• MERTAUGH,L. J. ,Jr.

Report Date:

1965-02-15

Pagination or Media Count:

198.0

Abstract:

The wind tunnel data resulting from a low speed wind tunnel test of a semi-span model of a close support, VTOL aircraft is presented. The model features an integrated propulsionlifting surface system as well as vertical and horizontal tails located on an aft, wing tip extension. The propulsion system exhaust flow, which is simulated with cold air, exhausts over the wing trailing edge flap flap jet and out of the lower surface of the wing wing box jet. The exhaust flows can be independently vectored through 90 degrees with respect to the wing chord plane. The test data are presented in the form of lift and rolling moment coefficients as functions of angle of attack, and drag and pitch moment coefficients as functions of lift coefficient. The coefficient data are given with and without the direct thrust contribution included. The static thrust data are given in the form of lift, drag, pitching moment and rolling moment as functions of angle of attack. No analysis of the data is presented. Author

Descriptors:

• WIND TUNNEL MODELS
• VERTICAL TAKEOFF AIRCRAFT
• WIND TUNNELS
• LIFT
• ROLL
• PITCH(MOTION)
• DRAG
• ANGLE OF ATTACK
• THRUST VECTOR CONTROL SYSTEMS
• PROPULSION SYSTEMS
• GAS FLOW

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE