A preliminary study of the effect on the wave drag of aerospikes placed on top of transonic wings has been presented. Since the Reynolds number formed with the diameter of the model of a cylindrical spike is relatively small when compared to real flight conditions the efficiency of the cylindrical spike was less than expected. In order to produce larger disturbances in the supersonic flow field above the wing spikes of other geometries have also been tested. For certain angles of attack a gain in lift and a reduction of drag has been observed. Thus, the concept of using aerospikes on transonic wings clearly shows a potential for reducing wave drag. The shape of the spikes needs a further optimization taking into account real flight Reynolds numbers. Furthermore, it is important to obtain more global information on the wave drag by perfoming wake-rake measurements at different lateral positions thus resolving the spanwise distribution of the sectional drag and determining the influence of the hold of the spike. In this several spikes should be arranged next to each other in spanwise direction on top of the wing. In future tests schlieren pictures may not be of primary importance. Then integral values of forces such as lift and drag can be directly obtained by using a wind tunnel balance.
Wave drag reduction by means of aerospikes on transonic wings
ISSW, International Symposium on Shock Waves, 26 ; 1309-1313
2009
5 Seiten, 5 Bilder, 8 Quellen
Aufsatz (Konferenz)
Englisch
Drag Reduction of Transonic Wings with Surrogate-Based Optimization
Springer Verlag | 2019
|Online Contents | 1998
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