STOVL Hot Gas Ingestion Control Technology

1989 ◽  
Author(s):  
K. C. Amuedo ◽  
B. R. Williams ◽  
J. D. Flood ◽  
A. L. Johns
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Scale Model ◽  
Nasa Lewis Research ◽  
Control Technology ◽  
Test Program ◽  
Hot Gas ◽  
Vertical Landing ◽  
Low Speed Wind Tunnel ◽  
Face Temperature

A comprehensive wind tunnel test program was conducted to evaluate control of Hot Gas Ingestion (HGI) on a 9.2% scale model of the McDonnell Aircraft Company model 279-3C advanced Short Takeoff and Vertical Landing (STOVL) configuration. The test was conducted in the NASA-Lewis Research Center 9 foot by 15 foot Low Speed Wind Tunnel during the summer of 1987. Initial tests defined baseline HGI levels as determined by engine face temperature rise and temperature distortion. Subsequent testing was conducted to parametrically evaluate HGI control using: Lift Improvement Devices (LIDs), forward nozzle splay angle, combination of LIDs and forward nozzle splay angle, and main inlet blocking. The results from this test program demonstrate that HGI can be effectively controlled and that HGI is not a barrier to STOVL aircraft development.

STOVL Hot Gas Ingestion Control Technology

1991 ◽  
Vol 113 (1) ◽  
pp. 68-74 ◽  
Author(s):  
K. C. Amuedo ◽  
B. R. Williams ◽  
J. D. Flood ◽  
A. L. Johns
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Scale Model ◽  
Nasa Lewis Research ◽  
Control Technology ◽  
Test Program ◽  
Hot Gas ◽  
Vertical Landing ◽  
Low Speed Wind Tunnel ◽  
Face Temperature

A comprehensive wind tunnel test program was conducted to evaluate control of Hot Gas Ingestion (HGI) on a 9.2 percent scale model of the McDonnell Aircraft Company model 279-3C advanced Short Takeoff and Vertical Landing (STOVL) configuration. The test was conducted in the NASA-Lewis Research Center 9 ft by 15 ft Low Speed Wind Tunnel during the summer of 1987. Initial tests defined baseline HGI levels as determined by engine face temperature rise and temperature distortion. Subsequent testing was conducted to evaluate HGI control parametrically using Lift Improvement Devices (LIDs), forward nozzle splay angle, a combination of LIDs and forward nozzle splay angle, and main inlet blocking. The results from this test program demonstrate that HGI can be effectively controlled and that HGI is not a barrier to STOVL aircraft development.

scholarly journals Investigation of the Time Dependence of Wind-Induced Aeroelastic Response on a Scale Model of a High-Rise Building

2021 ◽  
Vol 11 (8) ◽  
pp. 3315
Author(s):  
Fabio Rizzo
Keyword(s):  
Wind Tunnel ◽  
Time Dependence ◽  
Wind Tunnel Test ◽  
Structural Response ◽  
Cumulative Distribution ◽  
Scale Model ◽  
Acquisition Time ◽  
Test Results ◽  
High Rise ◽  
High Rise Building

Experimental wind tunnel test results are affected by acquisition times because extreme pressure peak statistics depend on the length of acquisition records. This is also true for dynamic tests on aeroelastic models where the structural response of the scale model is affected by aerodynamic damping and by random vortex shedding. This paper investigates the acquisition time dependence of linear transformation through singular value decomposition (SVD) and its correlation with floor accelerometric signals acquired during wind tunnel aeroelastic testing of a scale model high-rise building. Particular attention was given to the variability of eigenvectors, singular values and the correlation coefficient for two wind angles and thirteen different wind velocities. The cumulative distribution function of empirical magnitudes was fitted with numerical cumulative density function (CDF). Kolmogorov–Smirnov test results are also discussed.

Wind-Induced Responses Study and Wind-Resistant Design of Super-Long-Span Cable-Membrane Roof Structure of Shenzhen Baoan Stadium

2011 ◽  
Vol 71-78 ◽  
pp. 666-672
Author(s):  
Wen Bo Sun ◽  
Qing Xiang Li ◽  
Han Xiang Chen ◽  
Wei Jian Zhou
Keyword(s):  
Numerical Calculation ◽  
Wind Tunnel ◽  
Dynamic Response ◽  
Membrane Structure ◽  
Wind Tunnel Test ◽  
Scale Model ◽  
Induced Responses ◽  
Design Codes ◽  
Long Span ◽  
Roof Structure

In this paper, the system and the design philosophy of wheel-spoke cable-membrane structure of Baoan Stadium is introduced firstly. And then the study of wind tunnel test on 1:250 scale model is mainly presented, together with the numerical calculation of the wind dynamic response. Finally, the wind-resistant design of the roof structure based on the results of wind tunnel test and the foreign design codes is generally introduced.

STRUCTURAL DESIGN USING A WIND TUNNEL TEST PROGRAM AND A RISK ANALYSIS

1984 ◽  
pp. 27-36
Author(s):  
GARY C. HART ◽  
JON D. RAGGETT ◽  
SAMPSON HUANG ◽  
SUZANNE DOW
Keyword(s):  
Wind Tunnel ◽  
Risk Analysis ◽  
Structural Design ◽  
Wind Tunnel Test ◽  
Test Program

Feasibility investigation of large-scale model suspended by cable-driven parallel robot in hypersonic wind tunnel test

2016 ◽  
Vol 231 (13) ◽  
pp. 2375-2383 ◽  
Author(s):  
Xiaoguang Wang ◽  
Miaojiao Peng ◽  
Zhenghong Hu ◽  
Yueshi Chen ◽  
Qi Lin
Keyword(s):  
Wind Tunnel ◽  
Large Scale ◽  
Cfd Simulation ◽  
Aerodynamic Force ◽  
Wind Tunnel Test ◽  
Special Kind ◽  
Parallel Robot ◽  
Scale Model ◽  
Hypersonic Wind Tunnel ◽  
Large Scale Model

Cable-driven parallel robot is a special kind of robot, which is actuated by cables. It is already applied in the low speed wind tunnel to get aerodynamic measurement of aircraft model, and the aircraft pose could be adjusted by changing the cable length. Whether it can be used in hypersonic wind tunnel still needs further discussion. This paper presents the dynamics and aerodynamics analysis of a large-scale model supported by 6-DOF cable-driven parallel robot to investigate the feasibility of this special kind of suspension system in hypersonic wind tunnel. The description of this setup with a X-51A-like model is given, and then based on the system dynamic equations, aerodynamic force and stiffness matrix are derived. In the simulation, properties of dynamics and aerodynamics are mainly concerned. A typical shock tunnel with flow duration of about 100 milliseconds is taken as an example, and results show that the system is stable enough to meet the fundamental static wind tunnel test. From the cable tension variation under impact load and the sensitivity analysis, it is likely accessible to derive the aerodynamic forces. Compared with the sting suspension method, cable-driven parallel robot has the priority of higher inherent frequency and more flexible degrees. The interference to the flow field induced by cables is also preliminarily proved to be small by the CFD simulation, which can be acceptable and corrected. Researches conducted show the feasibility of cable-driven parallel robot’s application in hypersonic wind tunnel.

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