Adaptation of drag-rise charts in T.D. Memor. 71019 to the mid-semi-span portion of swept and tapered planforms.
Abstract:ESDU 72027 takes charts from ESDU 71019 for the prediction of the Mach number at which shock-wave drag first appears on families of aerofoils having a particular form of upper-surface pressure distribution at that drag rise condition and adapts them to three-dimensional flow. The adaptation applies to the mid-semi-span portion of a wing (away from the root, tip and any crank effects) of swept and tapered planforms having upper-surface pressure distributions in the streamwise direction equivalent to those of ESDU 71019. The adaptation uses simple sweep laws and equivalent sweep angle.
|Data Item ESDU 72027|
- 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