REVERSE THRUST PERFORMANCE OF A VARIABLE-PITCH FAN ENGINE AT FORWARD VELOCITY

被引：5
作者：
REEMSNYDER, DC
SAGERSER, DA
机构：
[1] NASA Lewis Research Center, Cleveland, OH
来源：
JOURNAL OF AIRCRAFT | 1979年 / 16卷 / 12期
关键词：
D O I：
10.2514/3.58612
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Variable-pitch fan engine was tested in the Ames 40 × 80 ft wind tunnel to determine the effect of forward velocity and crosswind on reverse-thrust peformance. Two flight-type inlet configurations were tested, and a flared fan nozzle was installed as an inlet for reverse-thrust operation. Steady-state reverse-thrust performance was obtained up to 54 m/s (105 knots). An abrupt decrease in reverse thrust occurred at about 30 m/s (60 knots). Reverse thrust was established following forward-to-reverse thrust transients both statically and with forward velocities up to 30 m/s. © 1979 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
引用
收藏
页码：848 / 855
页数：8
相关论文
共 10 条
  • [1] Ciepluch C.C., Quiet, Powered-Lift Propulsion, (1978)
  • [2] Sagerser D.A., Schaefer J.W., Dietrich D.A., Reverse-Thrust Technology for Variable Pitch Fan Propulsion Systems, Powered-Lift Aeronautics and Acoustics, pp. 387-402, (1976)
  • [3] Demers W.J., Metzger F.B., Smith L.W., Wainauski H.S., Testing of the Hamilton Standard Q-Fan Demonstrator, 1-2, (1973)
  • [4] Demers W.J., Nelson D.J., Wainauski H.S., Hamilton Standard Q-Fan Demonstrator Dynamic Pitch Change Test Program, 1, (1975)
  • [5] Demers W.J., Nelson D.J., Wainauski H.S., Hamilton Standard Q-Fan Demonstrator Dynamic Pitch Change Test Program, Vol. 2,”, 2, (1975)
  • [6] Schaefer J.W., Sagerser D.A., Stakolich E.G., Dynamics of High-Bypass-Engine Thrust Reversal Using a Variable-Pitch Fan, (1977)
  • [7] Giffin R.G., McFalls R.A., Beacher B.F., QCSEE Aerodynamic and Aeromechanical Performance of a 50.8 Cm (20 In.) Diameter, 1.34 PR, Variable-Pitch Fan with Core Flow, (1977)
  • [8] Reemsnyder D.C., Sagerser D.A., Effect of Forward Velocity and Crosswind on the Reverse-Thrust Performance of a Variable-Pitch Fan Engine, (1979)
  • [9] Wesoky H.L., Abbott J.M., Albers J.A., Dietrich D.A., Low-Speed Wind Tunnel Tests of a 50.8-Centimeter (20-In.) 1.15 Pressure Ratio Fan Engine Model, (1974)
  • [10] Keith T.G., Obee T.N., Dietrich D.A., Total Pressure Recovery of Flared Fan Nozzles Used as Inlets, Journal of Aircraft, 16, pp. 110-115, (1979)
1