First Results from GARTEUR AG-28 Transonic Wing/Body Code Validation Experiment

Kurzfassung

The GARTEUR Action Group 28 was established to provide developers and users of modern CFD codes with a high quality and highly accurate data base of a transonic wing/body configuration for validation purposes. Considering the advances in CFD code development, it was found necessary to not only provide the standard force and pressure data, but also more detailed flow field information from boundary layers and wakes. To ensure high quality and confidence in the results, experiments were to be performed at least in two different wind tunnels. To meet these requirements, the following wind tunnel experiments were carried out by the AG-28 partners Airbus Germany, Airbus France and Airbus UK, DLR, FOI, NLR, and ONERA: - pressure, forces, boundary layer and wake masurements in the S1MA facility on a large scale half-model (semi-span 3.7m) of an AS-28 configuration, representative for a modern megaliner configuration. An existing model was provided by Airbus France, refurbished, equipped with boundary layer probes and tested by ONERA. - precise force and pressure measurements with a full model of the same configuration in DNW HST, performed by NLR. A new cryogenic model was designed by DLR and manufactured by DLR, NLR and FOI. Special emphasis was put on accurate wall and far field sting interferences. - precise force and pressure measurements at different Reynolds numbers and model loadings (Q/E values). Besides providing a comparison with the HST results, the investigation of Reynolds number effects was here of course of special interest. The tests were carried out in 2001 (S1), 2002 (HST), and 2003 (ETW). Main test cases were the design point and a slightly off-design condition at a higher Mach number, where separation starts to occur on the upper side of the wing. Data analysis and comparison is currently under the way. So far, the target of a high quality data base seems to be achievable. The scatter of the results is very low, comparisons with older experiments with the half model in S1 show good agreement. Although the pressure tabs on the full model for one section had to be distributed to symmetric spanwise positions on both wings, the resulting composed pressure distributions are very smooth, indicating a good test quality. Final analysis is currently under the way. Final results and conclusion of AG-28 are foreseen for the end of 2003.