scholarly journals Night vision imaging systems design, integration, and verification in military fighter aircraft

2012 ◽  
Author(s):  
Roberto Sabatini ◽  
Mark A. Richardson ◽  
Maurizio Cantiello ◽  
Mario Toscano ◽  
Pietro Fiorini ◽  
...  
Keyword(s):  
Systems Design ◽  
Night Vision ◽  
Imaging Systems ◽  
Fighter Aircraft ◽  
Design Integration

scholarly journals Experimental Flight Testing of Night Vision Imaging Systems in Military Fighter Aircraft

2013 ◽  
Vol 42 (1) ◽  
pp. 20120339 ◽  
Author(s):  
Roberto Sabatini ◽  
Mark A. Richardson ◽  
Maurizio Cantiello ◽  
Mario Toscano ◽  
Pietro Fiorini ◽  
...  
Keyword(s):  
Night Vision ◽  
Imaging Systems ◽  
Flight Testing ◽  
Fighter Aircraft

Dynamic Inlet Simulation Demonstration for Airframe-Propulsion Integration Using HPCMP CREATE™-AV Kestrel

2017 ◽  
Author(s):  
Jason B. Klepper ◽  
James R. Sirbaugh ◽  
Milt W. Davis
Keyword(s):  
Mach Number ◽  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Systems Design ◽  
Computational Results ◽  
Military Aircraft ◽  
Fighter Aircraft ◽  
Inlet System ◽  
Weapon Systems ◽  
Dynamic Hybrid

The purpose of an aircraft inlet system is to capture airflow from the free-stream and deliver it to an engine at the appropriate Mach number for that system. To meet design constraints, modern fighter aircraft have complex inlets with multiple turns that generally lead to both total pressure and swirl distortion at the engine face. These flow distortions can lead to reduced system performance, operability, and durability introducing issues in the overall success of the weapons system performing its mission. Therefore the integration of the airframe, inlet, and propulsion system is a key design issue in the development of military aircraft. The purpose of this paper is to demonstrate the dynamic (hybrid RANS/DDES) simulation capabilities of the HPCMP CREATE™-AV Kestrel tools by application to a sub-scale airframe/inlet system for a current military aircraft. The computational results were compared to wind tunnel results at various Mach number, angles of attack, angles of sideslip, and corrected flow rates. The inlet pressure recovery and distortion intensities for each case compared well to wind tunnel results. By comparing the computational results and wind tunnel test results, the applicability of these tools to future weapon systems design and development can be assessed.

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