ESDU 73006 provides a method of estimating the rolling moment due to sideslip for a wing-fuselage-nacell
e configuration in low-speed attached flow. The wing alone contribution is first obtained from ESDU Aero A.06.01.03, ESDU Aero A.06.01.09 and ESDU 80033. ESDU 73006 gives the method of estimating the fuselage component, as a function of incidence, and the component due to wing-fuselage interference which is primarily a function of the wing height on the fuselage. The accuracy of the method is assessed by comparison with many test data for various configurations. For the effect of nacelles only a few data were available for models tested both with and without free flow nacelles and they suggest that rear fuselage mounted nacelles have no significant effect. A method for estimating the contribution due to two underwing mounted nacelles/pylons, which is a function of nacelle width and distance below the wing, is given,. It makes use of the sideforce due to sideslip estimated from ESDU 79006 to which is added an empirically-modified contribution from the theoretical antisymmetric incidence loading induced across the wing span by the nacelles, which depends on nacelle lateral position and distance below the wing. Configurations with four nacelles are treated by summing the effects of two pairs. The ranges of geometry with which comparisons were made are indicated.
ESDU 73006 provides a method of estimating the rolling moment due to sideslip for a wing-fuselage-nacelle configuration in low-speed attached flow. The wing alone contribution is first obtained from ESDU Aero A.06.01.03, ESDU Aero A.06.01.09 and ESDU 80033. ESDU 73006 gives the method of estimating the fuselage component, as a function of incidence, and the component due to wing-fuselage interference which is primarily a function of the wing height on the fuselage. The accuracy of the method is assessed by comparison with many test data for various configurations. For the effect of nacelles only a few data were available for models tested both with and without free flow nacelles and they suggest that rear fuselage mounted nacelles have no significant effect. A method for estimating the contribution due to two underwing mounted nacelles/pylons, which is a function of nacelle width and distance below the wing, is given,. It makes use of the sideforce due to sideslip estimated from ESDU 79006 to which is added an empirically-modified contribution from the theoretical antisymmetric incidence loading induced across the wing span by the nacelles, which depends on nacelle lateral position and distance below the wing. Configurations with four nacelles are treated by summing the effects of two pairs. The ranges of geometry with which comparisons were made are indicated.
