Boundary layer transition analysis of the scaled supersonic experimental airplane

Boundary layer transition characteristics of the scaled supersonic experimental airplane was numerically analyzed to confirm its Natural Laminar Flow (NLF) wing design. Using conventional incompressible and newly developed compressible transition prediction codes based on an e(sup N) method, the NLF characteristics were well confirmed though the following results. (1) The step function type target pressure distribution applied in the NLF wing design was found to be optimum (2) Comparing the transition N value estimated by the compressible code with experimental results obtained by NASA, wide laminar region of the NLF wing was expected. (3) Laminar boundary layer profiles estimated by a Navier-Stokes code led to smaller N value than one by the compressible boundary layer code. (4) No transition due to attachment-line contamination was predicted.
JAXA Special Publication
宇宙航空研究開発機構特別資料