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3‐D Inviscid Transonic Condensing Flow around a Swept Wing
Author(s) -
Goodheart K.A.,
Dykas S.,
Schnerr G.H.
Publication year - 2003
Publication title -
pamm
Language(s) - English
Resource type - Journals
ISSN - 1617-7061
DOI - 10.1002/pamm.200310171
Subject(s) - transonic , swept wing , naca airfoil , mechanics , trailing edge , wing , drag , leading edge , airfoil , inviscid flow , wing loading , mach number , angle of attack , materials science , adiabatic wall , drag coefficient , choked flow , supersonic speed , geometry , physics , reynolds number , aerodynamics , thermodynamics , mathematics , turbulence , boundary layer
Transonic condensing flow is an interesting phenomena because of the large change in temperature over a small area. This drop in temperature allows the moist air to condense. It is the purpose of this paper to examine the effect of sweep on condensing flow. The geometry of the wing model starts with NACA‐0014 at the wall and reduces to a NACA‐0010 at the tip. The span of the wing is 2.5 times the maximum chord length. The effect of sweep is examined by comparing a model wing with a sweep angle of 11.3 with a straight trailing edge that has no thickness and then a straight leading edge with a 11.3 trailing edge sweep. The free stream Mach number is 0.8 and angle of attack is 0. A 2‐D calculation shows that the NACA‐0014 and NACA‐0010 have a region of supersonic flow but due to the effect of sweep the sonic line does not extend to the tip. This change of the supersonic region influences the area of condensation on the wing. The swept wing has a lower total drag coefficient for the adiabatic and all condensation cases compared to the straight leading edge wing and second for the each wing the trend of increasing drag with humidity is shown.