Upwash interference for wings in solid-liner wind tunnels using subsonic linearised-theory.
Abstract:ESDU 95014 gives graphs, for a range of dimensions (relative to the span) of the rectangular section, of the spanwise variation of the interference upwash along the leading- and trailing-edges and mid-chord line of 66 transformed (to take account of compressibility) plane wing planforms (of which six are swept-forward). Mean values over the planform are also tabulated together with corrections to incidence such that values of lift and (vortex) drag are unchanged between wind tunnel and free-air. The aerodynamic centre positions and their aft shifts due to non-uniformity of upwash are also given. A Fortran program, ESDUpac A9514, provides a database of those results for ease of access. Use of the data for cambered and/or twisted wings and for test sections with corner fillets is considered and they may be applied to half- or full-wing tests. By use of the equivalent wing concept, they may also be used for wings with kinked leading- or trailing-edges and two examples are shown comparing results obtained using that concept with those calculated. The practical applicability of the results is discussed and they are expected to be satisfactory up to Mach numbers of 0.85 even in the presence of shocks or separation on the model.
|Data Item ESDU 95014|
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- Aircraft Noise
- Fatigue - Endurance Data
- Fatigue - Fracture Mechanics
- Fluid Mechanics, Internal Flow
- Fluid Mechanics, Internal Flow (Aerospace)
- Heat Transfer
- Physical Data, Chemical Engineering
- Stress and Strength
- Transonic Aerodynamics
- Vibration and Acoustic Fatigue
- Wind Engineering
Aerospace Materials Data
Additional Engineering References