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Tijdeman, H. (author), van Nunen, J.W.G. (author), Kraan, A.N. (author), Persoon, A.J. (author), Poestkoke, R. (author), Roos, R. (author), Schippers, P. (author), Siebert, C.M. (author)
A wind-tunnel investigation was carried out on an oscillating model of the F-5 wing with and without an external store (AIM-9J missile). Detailed steady and unsteady pressure distributions were obtained over the wing, while on the store total aerodynamic loads were measured. The tests covered the Mach number range between Ma = 0.6 and Ma = 1.35,...
report 1979
document
Tijdeman, H. (author), van Nunen, J.W.G. (author), Kraan, A.N. (author), Persoon, A.J. (author), Poestkoke, R. (author), Roos, R. (author), Schippers, P. (author), Siebert, C.M. (author)
A wind-tunnel investigation was carried out on an oscillating model of the F-5 wing with and without an external store (AIM-9J missile). Detailed steady and unsteady pressure distributions were obtained over the wing, while on the store total aerodynamic loads were measured. The tests covered the Mach number range between Ma = 0.6 and Ma = 1.35,...
report 1979
document
Tijdeman, H. (author), van Nunen, J.W.G. (author), Kraan, A.N. (author), Persoon, A.J. (author), Poestkoke, R. (author), Roos, R. (author), Schippers, P. (author), Siebert, C.M. (author)
A wind-tunnel investigation was carried out on an oscillating ng model of the F-5 wing with and without an external store (AIM-9J missile) . Detailed steady and unsteady pressure distributions were obtained over the wing, while on the store total aerodynamic loads were obtained. In addition, wind-tunnel wall pressures were measured. The tests...
report 1978
document
Tijdeman, H. (author)
Exploratory wind-tunnel experiments in high-subsonic and transonic flow on a conventional airfoil with oscillating flap and a supercritical airfoil oscillating in pitch are described. In the analysis of the experimental results, emphasis is placed upon the typical aspects of transonic flow, namely the interaction between the steady and unsteady...
report 1977
document
Tijdeman, H. (author), Schippers, P. (author), Persoon, A.J. (author)
Results are presented of unsteady pressure measurements on a two-dimensional model of the supercritical NLR 7301 airfoil performing pitching oscillations about an axis at ItO per cent of the chord. Paper presented at the Specialists' Meeting on Unsteady Airloads in Separated and Transonic Flow in conjunction with the 44th meeting of the...
report 1977
document
Tijdeman, H. (author)
report 1976
document
Tijdeman, H. (author)
Results are presented of measurements of the periodical motion of the shock waves on a NACA 64AOO6 airfoil with harmonically oscillating flap in two-dimensional attached transonic flow. It is shown that three different types of shock wave motion can be distinguished. An analytical model is developed, with which a satisfactory explanation can be...
report 1975
document
Tijdeman, H. (author)
Based on experimental observations an illustration is given of typical effects occiirring in high subsonic and transonic flow around oscillating airfoils and wings. It is shown that in this speed regime the unsteady airloads are influenced considerably by the interaction of the steady and unsteady flow fields. Moreover the periodical motion of...
report 1975
document
Tijdeman, H. (author)
Results are presented of measurements of the periodical motion of the shock waves on a NACA 64A006 airfoil with oscillating flap in two-dimensional attached transonic flow. It is shown that three different types of shock wave motion can be distinguished. An analytical model is developed, with which a satisfactory explanation can be given of the...
report 1975
document
Tijdeman, H. (author)
report 1974
document
Destuynder, R. (author), Tijdeman, H. (author)
On recommendation of the Working Group on Unsteady Aerodynamics of the AGARD Structures and Materials Panel, an investigation has been performed on a swept wing oscillating in subsonic flow. The primary objective of the investigation was to compare two different techniques for unsteady pressure measurements, In addition experimental data were...
report 1973
document
Tijdeman, H. (author), Schippers, P. (author)
report 1973
document
Tijdeman, H. (author), Zwaan, R.J. (author)
Possibilities to develop calculation methods for oscillating wings in transonic flow are discussed. Special attention is given to the question of linearisation. Recent NLR results of pressure measurements on an aerofoil with flap in transonic flow are analysed. Correlations are made between steady, quasi-steady and unsteady results. Shock motion...
report 1973
document
Tijdeman, H. (author), Bergh, H. (author)
An experimental investigation has been performed, which revealed a considerable difference between the dynamic response characteristics of a tube-trauisducer system with the entrance in still air and one having an airflow across the entrance orifice, The differences observed could be explained theoretically by modifyink the existing calculation...
report 1972
document
van Nunen, J.W.G. (author), Persoon, A.J. (author), Tijdeman, H. (author)
Ii!easurements were carried out on a model of a twin—bridge to determine the instationary aerodynaaic loads needed to perform stability calculations. The measuring procedure, based on an inertia compensated balance system, has been described and to demonstrate the applicability thereof, some results are presented and discussed. Paper presented...
report 1971
document
Tijdeman, H. (author), Zwaan, R.J. (author)
A kernel function method for calculating pressure distributions over wings with harmonically oscillating control surfaces in subsonic flow is briefly discussed. Comparisons of calculated and measured pressure distributions are given for different planforns, Mach numbers and reduced frequencies. An analysis is presented of pressure distributions...
report 1970
document
Bergh, H. (author), Tijdeman, H. (author), Zwaan, R.J. (author)
An analysis is given of pressure distributions measured on a swept wing model with harmonically oscillating control surface at subsonic to supersonic Mach numbers and at various frequencies. The influence of Mach number and finite span effects is discussed. Some comparisons are made with pressure distributions on a two-dimensional wing and with...
report 1970
document
Bergh, H. (author), Tijdeman, H. (author)
A number of comparative flutter calculations for a two-dimensional wing-control surface system has been performed to demonstrate the usefulness of empirical formulae for the control surface derivatives. Furthermore attention has been paid to the influence of the chord ratio T on the flutter behaviour and to the sensitivity of the system to each...
report 1968
document
Tijdeman, H. (author), Bergh, H. (author)
At this moment little experimental material is available about the instationary aerodynamic forces on wing-control surface combinations in high subsonic and transonic flow. Up to now the investigations on this subject have been restricted mainly to the determination of overall hinge moments by means of free oscillation techniques and to the...
report 1967
document
Tijdeman, H. (author)
report 1966
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