STOL Fighter Technology Program

1983 ◽  
Author(s):  
David R. Selegan
Keyword(s):  
Air Force ◽  
Landing Gear ◽  
Two Dimensional ◽  
High Lift ◽  
Technology Program ◽  
Thrust Vectoring ◽  
Design Task ◽  
Advanced Technologies ◽  
Propulsion Control ◽  
Near Term

In recent years, the Air Force has provided additional funds to investigate the technologies and problems associated with providing fighters a Short Take Off and Landing (STOL) capability without seriously degrading today’s maneuver, load, and cruise performance. Within the Flight Dynamics Laboratory, this technology thrust has been planned and organized under the title of “Runway Independence.” The thrust is multi-disciplined in that the following technologies are being investigated both singularly and in integrated combinations to quantify their contribution to providing options in solving the STOL design task. These technologies are: aerodynamics, integrated controls, thrust vectoring/reversing exhaust nozzles, landing gear, and cockpit aids and controllers necessary to operate under weather and/or at night. To help focus these technology efforts and to mature existing technology, the STOL Technology Fighter program was formulated. The objective of the program is to flight validate and mature near-term advanced technologies applicable to providing a STOL capability without sacrificing today’s maneuver, cruise or dash performance. Specific technologies to be addressed in this program are: two-dimensional thrust vectoring/reversing exhaust nozzle; integrated flight/propulsion control; advanced high lift systems; rough/soft field landing gear; and cockpit aids and controllers necessary to locate and land a fighter on the usable portion of the runway at night and in weather. The program will either modify an existing fighter like the F-15, F-16 or F-18 or build a hybrid vehicle like the X-29 with these technologies integrated into the vehicle. The contract will be awarded in 1983 with first flight in late 1987. The end objective of the program is to demonstrate take offs and landings under wet runway conditions of under 1500 feet including dispersion. This paper discusses the integration of these technologies into a total flight program.

Integrating a Systems Analysis Approach within Aircraft Maintenance Environments

1998 ◽  
Vol 42 (18) ◽  
pp. 1326-1330
Author(s):  
D. A. Mitta ◽  
L. Quill ◽  
B. L. Masquelier ◽  
P. A. Pohle
Keyword(s):  
Human Factors ◽  
Air Force ◽  
Systems Analysis ◽  
Research Laboratory ◽  
Technical Information ◽  
Analysis Approach ◽  
Task Environment ◽  
Advanced Technologies ◽  
Depot Maintenance ◽  
Air Force Research Laboratory

The Crew Survivability and Logistics Division of the Air Force Research Laboratory (AFRL/HES) is currently directing a program of research focused on enhancing the task environment for programmed depot maintenance (PDM) technicians. One issue being addressed by the Integrated Technical Information for the Air Logistics Centers (ITI-ALC) program is the appropriate insertion of advanced technologies into the PDM task environment. One challenge facing AFRL/HES was to identify those PDM functions for which the insertion of ITI-ALC technologies would be most beneficial. This paper describes how the application of a traditional human factors-based systems analysis led to the identification of these functions.

Automated CFD Analysis of Two-Dimensional High-Lift Flows

2002 ◽  
Vol 39 (4) ◽  
pp. 662-667 ◽  
Author(s):  
Anutosh Moitra
Keyword(s):  
Cfd Analysis ◽  
Two Dimensional ◽  
High Lift

scholarly journals Towards Advanced Fusion Gyrotrons: 2018 Update on Activities within EUROfusion

2019 ◽  
Vol 203 ◽  
pp. 04007
Author(s):  
John Jelonnek ◽  
Gaetano Aiello ◽  
Stefano Alberti ◽  
Konstantinos Avramidis ◽  
Alex Bruschi ◽  
...  
Keyword(s):  
Cvd Diamond ◽  
Current Drive ◽  
Coaxial Cavity ◽  
Diamond Disk ◽  
Advanced Technologies ◽  
Steady State Operation ◽  
Near Term ◽  
Long Pulse ◽  
System Operating

During the ongoing pre-concept phase (2014 – 2020) for a possible future European DEMOnstration Fusion Power Plant (DEMO) the activities within EUROfusion WP HCD EC Gyrotron R&D and Advanced Developments are focusing on options for near-term solutions, and, at the same time, on long-term even more advanced options. The near-term target for DEMO is to realize pulsed operation. According to the current baseline it will probably use an EC system operating at 170 GHz and 204 GHz is being assessed, whereas the long-term target aims for steady-state operation and frequencies for current drive up to 240 GHz. Common targets for both are an RF output power per unit of significantly above 1 MW (target: 2 MW) and a total gyrotron efficiency of significantly higher than 60 %. Frequency step-tunability and multi-purpose/multi-frequency operation have to be considered. Those targets shall be achieved by considering the coaxial-cavity gyrotron technology and advanced technologies for key components (e.g. CVD diamond-disk Brewster angle window). Advanced simulation and test tools are complementing the research and developments. Gyrotron development is additionally supported by a significant investment into a new multi-megawatt long-pulse gyrotron test stand which is under final installation at KIT currently.

scholarly journals Predicting Far-Field Noise Generated by a Landing Gear Using Multiple Two-Dimensional Simulations

2019 ◽  
Vol 9 (21) ◽  
pp. 4485
Author(s):  
Sultan Alqash ◽  
Sharvari Dhote ◽  
Kamran Behdinan
Keyword(s):  
Cross Sections ◽  
Near Field ◽  
Computational Cost ◽  
Numerical Data ◽  
Landing Gear ◽  
Design Stage ◽  
Far Field ◽  
Two Dimensional ◽  
Acoustic Analogy ◽  
Field Noise

In this paper, a new approach is proposed to predict the far-field noise of a landing gear (LG) based on near-field flow data obtained from multiple two-dimensional (2D) simulations. The LG consists of many bluff bodies with various shapes and sizes. The analysis begins with dividing the LG structure into multiple 2D cross-sections (C-Ss) representing different configurations. The C-Ss locations are selected based on the number of components, sizes, and geometric complexities. The 2D Computational Fluid Dynamics (CFD) analysis for each C-S is carried out first to obtain the acoustic source data. The Ffowcs Williams and Hawkings acoustic analogy (FW-H) is then used to predict the far-field noise. To compensate for the third dimension, a source correlation length (SCL) is assumed based on a perfectly correlated flow. The overall noise of the LG is calculated as the incoherent sum of the predicted noise from all C-Ss. Flow over a circular cylinder is then studied to examine the effect of the 2D CFD results on the predicted noise. The results are in good agreement with reported experimental and numerical data. However, the Strouhal number (St) is over-predicted. The proposed approach provides a reasonable estimation of the LG far-field noise at a low computational cost. Thus, it has the potential to be used as a quick tool to predict the far-field noise from an LG during the design stage.

scholarly journals High-fidelity simulations of unsteady civil aircraft aerodynamics: stakes and perspectives. Application of zonal detached eddy simulation

2014 ◽  
Vol 372 (2022) ◽  
pp. 20130325 ◽  
Author(s):  
Sébastien Deck ◽  
Fabien Gand ◽  
Vincent Brunet ◽  
Saloua Ben Khelil
Keyword(s):  
Turbulent Flows ◽  
Hybrid Methods ◽  
Landing Gear ◽  
High Fidelity ◽  
Detached Eddy Simulation ◽  
High Lift ◽  
Eddy Simulation ◽  
Civil Aircraft ◽  
Aircraft Aerodynamics ◽  
Transonic Buffet

This paper provides an up-to-date survey of the use of zonal detached eddy simulations (ZDES) for unsteady civil aircraft applications as a reflection on the stakes and perspectives of the use of hybrid methods in the framework of industrial aerodynamics. The issue of zonal or non-zonal treatment of turbulent flows for engineering applications is discussed. The ZDES method used in this article and based on a fluid problem-dependent zonalization is briefly presented. Some recent landmark achievements for conditions all over the flight envelope are presented, including low-speed (aeroacoustics of high-lift devices and landing gear), cruising (engine–airframe interactions), propulsive jets and off-design (transonic buffet and dive manoeuvres) applications. The implications of such results and remaining challenges in a more global framework are further discussed.

Editorial on Future Jet Technologies

2014 ◽  
Vol 31 (4) ◽  
Author(s):  
Benjamin Gal-Or
Keyword(s):  
Flight Control ◽  
Landing Gear ◽  
Engineering Practice ◽  
Mobile Telecommunication ◽  
Fighter Aircraft ◽  
Thrust Vectoring ◽  
Jet Engine ◽  
Stealth Technology ◽  
Forced Landing ◽  
Expected Benefits

AbstractThe jet engine is the prime flight controller in post-stall flight domains where conventional flight control fails, or when the engine prevents catastrophes in training, combat, loss of all airframe hydraulics (the engine retains its own hydraulics), loss of one engine, pilot errors, icing on the wings, landing gear and runway issues in takeoff and landing and in bad-whether recoveries. The scientific term for this revolutionary technology is “jet-steering”, and in engineering practice – “thrust vectoring”, or “TV”.Jet-Steering in advanced fighter aircraft designs is integrated with stealth technology. The resulting classified Thrust-Vectoring-Stealth (“TVS”) technology has generated a second jet-revolution by which all Air-&-Sea-Propulsion Science and R&D are now being reassessed.ClassifiedOne, and perhaps a key conclusion presented here, means that bothMobile telecommunication of safe links between flyers and combat drones (“UCAVs”) at increasingly deep penetrations into remote, congested areas, can gradually be purchased-developed-deployed and then operated by extant cader of tens of thousandsWe also provide 26 references [17–43] to a different, unclassified technology that enhances TV-inducedExpected benefits include anti-terror recoveries from emergencies, like forced landing on unprepared runways or highways, or recoveries from all airframe-hydraulics-outs, asymmetric ice on wings, landing gear catastrophes, and recoveries from pilot errors and bad-whether incidents [Rule 9(7)].

Evaluation of RANS Transition Modeling for High Lift LPT Flows at Low Reynolds Number

2013 ◽  
Author(s):  
Kevin Keadle ◽  
Mark McQuilling
Keyword(s):  
Reynolds Number ◽  
Total Pressure ◽  
Current Model ◽  
Pressure Coefficient ◽  
Low Pressure ◽  
Two Dimensional ◽  
High Lift ◽  
Low Pressure Turbine ◽  
Low Reynolds ◽  
Turbine Airfoils

High lift low pressure turbine airfoils have complex flow features that can require advanced modeling capabilities for accurate flow predictions. These features include separated flows and the transition from laminar to turbulent boundary layers. Recent applications of computational fluid dynamics based on the Reynolds-averaged Navier-Stokes formulation have included modeling for attached and separated flow transition mechanisms in the form of empirical correlations and two- or three-equation eddy viscosity models. This study uses the three-equation model of Walters and Cokljat [1] to simulate the flow around the Pack B and L2F low pressure turbine airfoils in a two-dimensional cascade arrangement at a Reynolds number of 25,000. This model includes a third equation for the development of pre-transitional laminar kinetic energy (LKE), and is an updated version of the Walters and Leylek [2] model. The aft-loaded Pack B has a nominal Zweifel loading coefficient of 1.13, and the front-loaded L2F has a nominal loading coefficient of 1.59. Results show the updated LKE model improves predicted accuracy of pressure coefficient and velocity profiles over its previous version as well as two-equation RANS models developed for separated and transitional flows. Transition onset behavior also compares favorably with experiment. However, the current model is not found suitable for wake total pressure loss predictions in two-dimensional simulations at extremely low Reynolds numbers due to the predicted coherency of suction side vortices generated in the separated shear layers which cause a local gain in wake total pressure.

Thrust Vectoring Design Project at Six Universities: Part I — Project Description and Final Designs

2013 ◽  
Author(s):  
Mark G. Turner ◽  
Markus P. Rumpfkeil ◽  
James T. VanKuren ◽  
Rory A. Roberts ◽  
Jeffrey Bons ◽  
...  
Keyword(s):  
Air Force ◽  
Undergraduate Students ◽  
Outreach Program ◽  
Thrust Vectoring ◽  
Jet Engine ◽  
Us Air Force ◽  
Project Description ◽  
The Us ◽  
Air Force Research Laboratory ◽  
Academic Year

An undergraduate student design and build project has been established by the US Air Force, Air Force Research Laboratory as part of an outreach program. During the 2011–2012 academic year, undergraduate students of six universities participated in designing a thrust vectoring system for a small (20 pound-thrust) jet engine. A description of the project parameters and student designs is given in this paper. It proved to be an extremely successful project, and other professors and students can learn from the different approaches taken by the six different teams and the project itself. Industry will also be interested in the depth and breadth of an undergraduate project that is being used to educate their future engineering workforce.

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