Publication Date:
2004-12-03
Description:
An improved laminar run and trip drag correction methodology for supersonic cruise performance testing was derived. This method required more careful analysis of the flow visualization images which revealed delayed transition particularly on the inboard upper surface, even for the largest trip disks. In addition, a new code was developed to estimate the laminar run correction. Once the data were corrected for laminar run, the correct approach to the analysis of the trip drag became evident. Although the data originally appeared confusing, the corrected data are consistent with previous results. Furthermore, the modified approach, which was described in this presentation, extends prior historical work by taking into account the delayed transition caused by the blunt leading edges.
Keywords:
Aerodynamics
Type:
1999 NASA High-Speed Research Performance Workshop; Volume 1; Part 2; 1163-1196; NASA/CP-1999-209704/VOL1/PT2
Format:
text
