ESDU Aero A.02.03.02:

Optimum area distribution and associated minimum theoretical transonic drag-rise for aircraft at zero lift.

Optimum area distribution and associated minimum theoretical transonic drag-rise for aircraft at zero lift.

This program calculates the minimum theoretical transonic drag rise of a wing-body combination of optimum area distribution using the method of ESDU Aero A.02.03.02 . The method applies to configurations having two mutually perpendicular planes of symmetry the intersection of which define the longitudinal axis of the configuration, and there may be an intake, provided there is no spillage, and a jet orifice. (In the Data Item, a method is suggested for dealing with the case when the intake and jet orifice are not respectively at the nose and base of the body.)

The configuration is defined by its nose and base areas, its length, its volume and a cross-sectional area and its distance from the nose. The base area must exceed the nose area; if that is not the case, the configuration must be reversed before making the calculations. The method represents the optimum area distribution as the sum of three distributions each making a separate contribution to the drag rise. It is possible for either the chosen value of cross-sectional area or the volume to be smaller than the optimum values; in either case one of the area distributions makes no contribution to the drag rise.

The Data Item should be consulted for full descriptions of the parameters, the method and its derivation.

Results
: Warning - the input has changed! Rerun the calculation
contain errors or warnings

Save results as

The calculation produced invalid results. However, these results are
presented here in order to aid the understanding of the invalid body
area distributions imposed by the given geometrical data.

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tba:

{{tba | json}}