Publication Date:
2019-07-13
Description:
The effect of descent rate (DR) on the approach aerodynamics of the F-15 S/MTD aircraft is investigated experimentally using a moving model in the NASA Langley Vortex Research Facility. A 0.083-scale low-speed rotary-balance model equipped with a thrust-reverser simulator and with grit strips to assure turbulent flow was tested in an approach configuration at forward speed 60 ft/sec, corresponding to DR = 4.19 ft/sec. The results are presented in extensive graphs and compared with wind-tunnel data on the same configuration at DR = 0. Significant differences are attributed to the DR in the present experiments and the presence of a ground boundary layer in the wind-tunnel tests. It is predicted that safe approaches could be made with the lower thrust reverser vectored up to 80 deg, or even 110 deg if the DR were not arrested near the ground.
Keywords:
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Type:
AIAA PAPER 89-3280
,
AIAA Flight Simulation Technologies Conference and Exhibit; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
Format:
text
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