HEAVY-LIFT TIP TURBOJET ROTOR SYSTEM. VOLUME 2. PARAMETRIC DESIGN STUDY

1965 ◽  
Author(s):  
HILLER AIRCRAFT CORP PALO ALTO CA
Keyword(s):  
Parametric Design ◽  
Rotor System ◽  
Design Study ◽  
Heavy Lift ◽  
System Volume

HEAVY-LIFT TIP TURBOJET ROTOR SYSTEM. VOLUME 1

1965 ◽  
Author(s):  
HILLER AIRCRAFT CORP PALO ALTO CA
Keyword(s):  
Rotor System ◽  
Heavy Lift ◽  
System Volume

40,000-POUND-CAPACITY HEAVY-LIFT HELICOPTER EXTERNAL CARGO HANDLING SYSTEM DESIGN STUDY

1968 ◽  
Author(s):  
Robert V. Patterson ◽  
Fred J. Fisch ◽  
Hans D. Heyck ◽  
Richard L. Jarvis ◽  
Barron W. Mouring
Keyword(s):  
System Design ◽  
Design Study ◽  
Handling System ◽  
Cargo Handling ◽  
Heavy Lift

scholarly journals Parametric Design Study on Aerodynamic Characteristics of Variable Pitot Inlets for Transonic and Supersonic Civil Aviation

2019 ◽  
Vol 304 ◽  
pp. 02017 ◽  
Author(s):  
Stefan Kazula ◽  
Mark Wöllner ◽  
David Grasselt ◽  
Klaus Höschler
Keyword(s):  
Design Space ◽  
Parametric Design ◽  
Aerodynamic Characteristics ◽  
Geometric Parameters ◽  
Civil Aviation ◽  
Potential Range ◽  
Design Study ◽  
Aero Engine ◽  
Inlet Length ◽  
Evaluation Parameters

This paper reveals the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. The trade-off in inlet design and aerodynamic evaluation parameters are presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additional weight, the inlet length represents the parameter with the highest potential for drag reduction by up to 50% in the selected design space. Ideal geometries for variable pitot inlets are determined. After considering weight, their potential range benefit nearly disappears for subsonic applications, but remains above 20% for supersonic flight at Mach 1.6.

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