Searched for: subject%3A%22Windtunnels%22
(1 - 11 of 11)
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Smeur, E.J.J. (author), de Croon, G.C.H.E. (author), Chu, Q. P. (author)
This paper presents the cascaded integration of Incremental Nonlinear Dynamic Inversion (INDI) for attitude control and INDI for position control of micro air vehicles. Significant improvements over a traditional Proportional Integral Derivative (PID) controller are demonstrated in an experiment where the quadrotor flies in and out of a 10 m...
journal article 2018
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Van Oudheusden, B.W. (author)
book 1998
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Reichelsdorfer, P (author), Bateman, D.P. (author), Corben, T. (author)
report 1995
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Bos, J.F.T. (author), Faasse, P.R. (author)
The High Speed wind Tunnel (HST) of the National Aerospace Laboratory NLR is one of the major transonic windtunnels and is used for aerodynamic research on scale models. The measurements require the control of the Mach number. Two kinds of controller tasks can be distinguished: keeping the Mach number constant, and realizing a different Mach...
report 1992
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Conradi, Torsten (author), Neubelt, Frank (author)
report 1989
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den Boer, R.G. (author)
An experimental investigation revealed that the d5mamic response of a given pressure tube depends not only on the mean local pressure and the frequency, but also on the pressure amplitude and the boundary-layer at the tube entrance. By analyzing the flow at the entrance of the tube, the parameters are determined, which possibly play a role in...
report 1988
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van Beek, C.M. (author)
The application of a boundary integral or "panel" method to duct flows is described. The method is capable of computing the three dimensional, steady state, subsonic, linearized (Prandtl-Glauert) potential flow about general configurations. The method is characterized by the application of a Dirichlet boundary condition and of "compressible"...
report 1987
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Labrujere, T.E. (author)
A description is given of a method for the determination of global corrections for wall interference in both solid- and ventilated wall windtunnels, 2D as well as 3D. The method is based on the assumption that the flow velocity is known at a control surface surrounding the model and that the main part of the flow field may be considered...
report 1984
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Doornbos, G. (author), de Wolf, W.B. (author)
A wind tunnel test procedure is described to determine from the thrust minus drag measurements the aircraft drag and engine/airframe interference drag at cruise conditions. The definitions of the thrust and drag terms in use are given. Engine thrust simulation is provided by a calibrated Turbofan Powered Simulator (TPS). Further the use of a...
report 1982
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Ross, R. (author), Rohne, P.B. (author)
Measurements of flow disturbances in the NLR - HST on the centerline and at the sidewall showed a maximiun noise level of 1 % in Cprms at a Mach number of 0.8. This is low compared with other ventilated wall tunnels of about the same size. Space-time correlations showed that a large part of the flow disturbances concisted of upstream travelling...
report 1973
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de Vos, D.M. (author)
An investigation on a two-dimensional wing model with a double-slotted trailing edge flap is described where tunnel wall boundeo'y layer control by blowing was applied to prevent premature flow separations at the junctions between the model and the tunnel walls. From the results it is concluded that tunnel wall boundary layer control at the wall...
report 1973
Searched for: subject%3A%22Windtunnels%22
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