DESIGN OF AERODYNAMIC TEST FACILITIES | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 10, Volume 1, A.S.A.T. CONFERENCE 14-16 May 1985 r CAIRO, May 1985, Page 109-140 PDF (9.84 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.1985.26470 | ||||
 View on SCiNiTO | ||||
| Author | ||||
| JOHN ROSEN | ||||
| Managing Director, AB Rollab, Aviatest/Rollab, Stockholm, Sweden. | ||||
| Abstract | ||||
| Very simple and basic theoretical considerations will determine the design features of an aerodynamic facility. Desired Speed/Mach Number range, flight altitudes, Reynolds No etc. will call for different tunnel requirements with regard to model size, tempe-ratures, pressures and energy supply. For certain types of tests there will be special limitations which will be defined and discussed. Restrictions can be of an economic as well as of a physical nature. High temperature simulation, stability and flutter belong to this category. An attempt will be made to give a survey of expedient combinations of e-quipment and devices for covering this vast area of aerodynamic testing. In the original planning of an aerodynamic facility it must be decided upon a long term stategy so that an optimum solution - with alternative development potentials - could be realized in stages. In such basic facilities, the objectives can easily be changed and acconi modated to comply with new strategies or R & D policies. | ||||
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