Narayan, KY and Hartmann, K (1988) Transonic and supersonic flow past a 65xB0; delta wing with rounded leading edges - analysis of experimental data. Technical Report. National Aeronautical Laboratory, Bangalore, India.
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Abstract
Available experimental data on a 65xB0; swept back cropped delta wing with rounded leading edges have been analysed, the experimental data cover a Mach number range of 0.4 to 4 and include results from the DFVLR Transonic Wind Tunnel (TWG) at Goettingen and the NLR High Speed (HST) and Supersonic (SST) Wind Tunnels at Amsterdam. The tests at a Mach number of 0.85 cover a Reynolds number range of 2.4 to 13 million. The extensive static pressure data have been analysed in detail. Based on limited surface flow13; visualization results, three basic flow types have been identified - fully attached flow, mixed flow and leading edge separated flow. The mixed type of flow has been further sub-classified into three types depending on the location of separation. The results show that flow attachment at the rounded leading edge occurs at a lower Mach number compared to a wing with sharp leading edge. Also, leading edge separation on a wing with a drooped leading edge occurs at an angle of attack which is higher compared to that of the undrooped case by an angle approximately equal to the droop. It is shown that the Reynolds number has a significant effect on the boundaries between the different types of flow. In particular, an increase in Reynolds number causes leading edge separation to occur at higher angles of attack.
| Item Type: | Monograph (Technical Report) |
|---|---|
| Additional Information: | This document is also available as DFVLR-FB-88-44 |
| Uncontrolled Keywords: | Delta wing;Leading edge separation;Leading edge vortices;Transonic flow;Supersonic flow |
| Subjects: | AERONAUTICS > Aerodynamics |
| Depositing User: | Mr. Ravikumar R |
| Date Deposited: | 13 Sep 2006 |
| Last Modified: | 24 May 2010 04:20 |
| URI: | http://nal-ir.nal.res.in/id/eprint/2714 |
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