This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Engine Inlet Interaction with a Prop-Fan Propulsion System
ISSN: 0148-7191, e-ISSN: 2688-3627
Published October 01, 1984 by SAE International in United States
Annotation ability available
Pratt & Whitney participated in a cooperative model test program with NASA Lewis, Lockheed-Georgia and Hamilton Standard to evaluate chin inlet/propeller interactions using an advanced technology Prop-Fan model. The tests were conducted at the United Technologies Research Center's main wind tunnel using its propeller test rig and NASA Lewis's 2-ft diameter SR3 Prop-Fan model. The tests were done at several forward flight speeds, up to Mach 0.8, simulating both cruise and reverse thrust operation. Interaction effects with and without boundary layer diverters are discussed in terms of inlet recovery and installed thrust minus drag. These interaction effects are presented as a function of parameters such as power coefficient, advance ratio, mass flow ratio and Mach number.
CitationTanner, D. and Wynosky, T., "Engine Inlet Interaction with a Prop-Fan Propulsion System," SAE Technical Paper 841478, 1984, https://doi.org/10.4271/841478.
- Hinson B. L., “Design and Experimental Evaluation of Prop Fan Inlets”, 1984 SAE Aerospace Congress and Exposition, October, 1984.
- Black D. M., Menthe R. W., and Wainuuski H. S., “Aerodynamic Design and Performance Testing of an Advanced 30 Degree Swept, Eight Bladed Propeller at Mach Numbers from 0.2 to 0.85,” NASA CR3047, 1978.
- Rohrbach C., Metzger F. B., Black D. M. and Ladden R. M. “Evaluation of Wind Tunnel Performance Testing of an Advanced 45 Degree Swept Eight Bladed Propeller at Mach Numbers from 0.45 to 0.85,” NASA CR-3505, March, 1982.