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A simple method for the derivation of isolated and installed store loads

Published online by Cambridge University Press:  04 July 2016

S. H. Goudie
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Extract

As military aircraft become more multi-role in design, the use of externally carried ordnance has increased both in frequency and variety resulting in increased use of wind tunnels for store load measurement. It is intended that this report may be useful in predicting loads on a variety of isolated stores at speeds up to transonic and in providing loading data on a new store carried on an aircraft by converting wind-tunnel measurements made on an existing store.

The estimation of aerodynamic loads uses linear methods for forebody and fin-wing normal forces with cross-flow terms on body and fin and also tail recovery effects represented by higher-order predictions. Allowance is made for body to lifting surface and lifting surface to body carry-over effects. The effect of the location of the fins and wings with respect to the body and their dihedral is also accounted for in the prediction.

Type
Research Article
Information
The Aeronautical Journal , Volume 87 , Issue 869 , November 1983 , pp. 343 - 347
Copyright
Copyright © Royal Aeronautical Society 1983 

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References

1. Nielsen, J. N., Pitts, W. C. and Kaattari, G. E. Lift and Centre of Pressure of Wing-Body-Tail combinations at subsonic, transonic and supersonic speeds. NACA Report 1307.Google Scholar
2. Hoerner, S. F. Fluid Dynamic Lift, 19–10.Google Scholar
3. Hoerner, S. F. Fluid Dynamic Lift, 3–4.Google Scholar
4. Hoerner, S. F. Fluid Dynamic Lift, 20–8.Google Scholar
5. Spence, A. and Treble, W. J. G. Low Speed Tunnel Tests on the Flow Structure behind a Body of revolution of Fineness Ratio 16⅔:/1. RAE TN Aero 2406.Google Scholar
6. Polhamus, E. C. Charts for predicting Characteristics of Delta Wings. NASA TN D-4739.Google Scholar