In recent years there has been a renewed interest in the development of hypervelocity vehicles and such propulsion systems as the scramjet engine. Research into the aerodynamic characteristics of the blunted cone has relevance to the design of scramjet intakes. Research into such cones in subsonic and supersonic flight regimes is extensive, but in the hypervelocity regime this is not the case. A free-flight investigation of the aerodynamics of a blunted 10-deg semi-angle cone has been performed in a hyperballistic range. Impulse facilities, such as free piston driver shock tunnels, have been developed to enable investigation into both the hypersonic and hypervelocity regimes. The test time in these facilities of the order of 1 ms. This short test time prohibits force component measurement with conventional force or accelerometer balances. The stress wave force balance developed by Sanderson and Simmons relies on interpretation of the transient stress waves propagating within the model and its supporting structure. This approach accounts for the distributed mass effects of the model and force balance structure which are significant in short test times. Sanderson and Simmons applied the technique to a 15-deg semi-vertex angle cone which has a uniform surface pressure distribution and a large resulting drag force. Sanderson extended the technique to application to a longer cone of 5-deg semi-vertex angle. The magnitude of the drag force is smaller on the more slender cone. The work represents a further extension of the technique to measuring the drag due to non-uniform load distributions such as found over blunted bodies. Experiments were performed on a 5-deg semi-vertex angle cone with interchangeable nose tips. The cone had a base radius of 50 mm. Eleven different nose tips were used ranging in radius from 0.2 mm to 18.0 mm in steps of 1.8 mm. The length of the model with the pointed nose tips was 517.5 mm. All experiments were performed with the model aligned axially with the flow.
Shock tunnel measurements of hypervelocity blunted cone drag
Messung des Luftwiderstandes abgestumpfter Wirbelschleppen bei Hypergeschwindigkeit im Stoßwellenkanal
AIAA Journal ; 32 , 12 ; 2476-2477
1994
2 Seiten, 2 Bilder, 1 Tabelle, 7 Quellen
Article (Journal)
English
Shock Tunnel Measurements of Hypervelocity Blunted Cone Drag (TN)
Online Contents | 1994
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