Abstract
Skin friction measurements for a normal shock/boundary-layer interaction with and without an aeroelastic mesoflap control method have been conducted in a planar Mach 1.4 wind tunnel. The skin friction has been measured downstream of the interaction, using the laser interferometer skin friction (LISF) meter, which optically detects the rate of thinning of an oil film applied to the test surface. Several different configurations of the mesoflap arrays are tested, and the results are compared to the solid-wall reference case with no control mechanism. One particular flap array provides a higher skin friction downstream of the interaction, and as such tends to have a better recovery from flow separation as compared to the other flap arrays. However, all values of skh friction for the mesoflap arrays are found to be lower than for the solid-wall reference case. As such, the flow control system can be more susceptible to separation for this particular condition, but may reduce viscous drag in external flows. Velocity profiles measured by the LDV technique at the same locations in the interactions are also utilized to evaluate the skin friction, and it is found that comparison with the LISF data shows satisfactory agreement. A numerical simulation is also carried out for the identical flow conditions of the solid-wall case, and its results also show good comparison with the present experimental data.
| Original language | English (US) |
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| State | Published - 2002 |
| Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: Jan 14 2002 → Jan 17 2002 |
Other
| Other | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 1/14/02 → 1/17/02 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering