Aerodynamic centre of wing-fuselage combinations.
ESDU 76015 gives an empirical method for correcting the wing-alone aerodynamic centre position from ESDU 70011. Graphs give correction factors for fuselage forebody and afterbody length, and width, and fuselage height/width ratio. An equivalent wing is used, extending the net wing into the fuselage, and the method can be applied to wings with cranks (see also ESDU 76003). The method was derived from data from 32 configurations of aspect ratio 6 to 12, mid-chord sweeps up to 45 degrees, and taper ratios of 0.2 to 1 and it predicts the position to within 0.03 of aerodynamic mean chord. It is restricted to fully-attached subsonic flow and those incidences where the lift-curve slope is essentially linear.
The computer program ESDUpac A1309, associated with ESDU 13009, evaluates the chordwise position of the aerodynamic centre of wing-fuselage-nacelle combinations at subsonic speeds.
|Data Item ESDU 76015|
This program is only available to subscribers.
The graphs listed below are available only to subscribers.
|Figure 1||Effect of forebody and afterbody lengths|
|Figure 2||Effect of fuselage width|
|Figure 3a||Effect of wing sweepback. d/b = 0.08|
|Figure 3b||Effect of wing sweepback. d/b = 0.12|
|Figure 3c||Effect of wing sweepback. d/b = 0.16|
|Figure 4||Correction to wing sweepback effect|
- 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