ESDU AERO C.04.01.06
Fullspan control hingemoment coefficient derivatives for unswept wings in incompressible flow with allowance for spanwise variation of sectional properties.
Abstract:
ESDU Aero C.04.01.06 gives equations for the rates of change of hinge moment coefficient with incidence and with control deflection which include a spanwise integration of their respective values in twodimensional flow. Those twodimensional values may be obtained respectively from ESDU Aero C.04.01.01 and C.04.01.02 and if necessary may be corrected for the effect of nose or internal balance using ESDU Aero C.04.01.03 and C.04.01.04 respectively. Both equations involve parameters for which values have been calculated using liftingline theory applied to elliptical loading for unswept wings together with a correction factor for nonelliptical loadings and all the factors are presented graphically. The equations also involve respectively the sectional liftcurve slope and the sectional value of the slope of the lift coefficient curve with control deflection for which values may be obtained respectively from ESDU Aero W.01.01.05 and C.01.01.03. The equation for the rate of change of hinge moment with control deflection includes in addition the integration of the sectional value for the rate of change of hinge moment with incidence. For quantities not involved in the integrations, mean values are taken appropriate to the a mean section geometry. The method is illustrated with a fullyworked practical example.Indexed under:
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Data Item ESDU AERO C.04.01.06  

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This Data Item contains 6 interactive graph(s) as listed below.
Graph  Title 

Figure 1  Ratio of induced angle of attack to control deflection 
Figure 2  Streamline curvature contribution in equation (2.2) 
Figure 3a  Factor on G and G_{1} for Balance  Nose balance 
Figure 3b  Factor on G and G_{1} for Balance  Internal balance 
Figure 4a  Induced angle of attack ratio for straighttapered wings 
Figure 4b  Induced angle of attack ratio for wings with rounded tips 
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