Hostname: page-component-586b7cd67f-l7hp2 Total loading time: 0 Render date: 2024-11-25T19:14:27.520Z Has data issue: false hasContentIssue false
  • English
  • Français

Calculation of support interferences on the aerodynamic coefficients for a windtunnel calibration model

Published online by Cambridge University Press:  04 July 2016

D. Steinbach
D. Steinbach*
Affiliation:
Institut für Theoretische Strömungsmechanik, DLR Göttingen, Germany
Get access Rights & Permissions [Opens in a new window]

Summary

An AGARD calibration model has been tested in the subsonic cryogenic windtunnel (KKK) of DLR Köln, model support interferences are calculated in the form of corrections to the aerodynamic coefficients. Two different model support systems are investigated: the model mounted on a horizontal sting (rear sting), and the model mounted on a vertical sting (ventral sting). Since for these configurations earlier experiments already exist, the corrections obtained are applied to these measurements for further verification. Furthermore the sting influences on the longitudinal static stability of the model are investigated in more detail.

A 3D-panel method is used which allows simultaneous calculation of several displacing and lifting bodies of nearly arbitrary shapes in the flow. The aerodynamic coefficients are obtained by numerical integration of the surface pressure distribution on the model.

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 942 , February 1991 , pp. 55 - 63
Copyright
Copyright © Royal Aeronautical Society 1991 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Tinling, B. E. and Lopez, A. E. The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3.1. Effects of Horizontal Tail Location and Size on the Longitudinal Characteristics, NACA Technical Note 4041, 1957.Google Scholar
2. Savage, H. F. and Tinling, B. E. The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3. II. Lateral and Directional Characteristics, NACA Technical Note 4042, 1957.Google Scholar
3. Baumert, W. and Kühn, A. Six-Component Measurements on a Calibration Model in the 3x3 m2 low speed windtunnel of DFVLR Göttingen, DFVLR IB 16100-81 C 28, 1981.Google Scholar
4. Joosen, C. J. J. Calculated influence of the sting model support on the main aerodynamic coefficients, DNW-PA-82.003, 1982, German-Netherlands Windtunnel.Google Scholar
5. Amtsberg, J. Prediction of interference effects between model and sting support in a windtunnel by panel method, J Wind Eng Ind Aerodynam, 1984, 16, pp 351–360.Google Scholar
6. Carter, E. C. Interference effects of model support systems, AGARD-R-601 on “Problems in wind tunnel testing techniques”, Paper no. 3-1 to 3-10, 1973.Google Scholar
7. Loving, D. L. and Luoma, A. A. Sting Support Interference on Longitudinal Characteristics of Cargo-Type Airplane Models at Mach 0-70 to 0-84, NASA Technical Note D-4021, 1967.Google Scholar
8. Amtsberg, J. and Ramm, G. Berechnung der Umströmungeines beliebigen Körpers mit dem Panelverfahren, inkompressibles Verdrängungs- und Auftriebsproblem, DFVLR IB 129-84/2, 1984, Braunschweig.Google Scholar
9. Woodward, F. A. An improved method for the aerodynamic analysis of wing-body-tail configurations in subsonic and super-sonic flow, NASA CR-2228, Parts I and II, May 1973.Google Scholar
10. Heiss, S. and Fornasier, L. Analysis of a fighter type aircraft configuration with the HISSS panel method at subsonic and supersonic speeds, Z Flugwiss Weltraumforsch 1988, 12, pp 224–232.Google Scholar
11. Viehweger, G. Beitrag zu dem Problem der Stielinterferenz an Windkanalmodellen, DFVLR 157-77 A 30, 1978, Braunschweig.Google Scholar
12. Steinbach, D. Berechnung der Support Interferenzen für die aerodynamischen Beiwerte eines Windkanal-Eichmodells, DLR-FB 90-26, 1990.Google Scholar
13. Schlichting, H. and Truckenbrodt, E. Aerodynamics of the airplane, 1979, McGraw-Hill.Google Scholar