A method is developed to determine the flowfield of a body of revolution in separated flow. The technique employed is the use of the computer to integrate various solutions and solution properties of the sub-flowfields which make up the entire flowfield without resorting to a finite difference solution to the complete NavierStokes equations. The technique entails the use of the unsteady cross flow analogy and a new solution to the required two-dimensional unsteady separated flow problem based upon an unsteady discrete-vorticity wake. Data for the forces and moments on bodies of revolution at high angle of attack (outside the range of linear inviscid theories) such that the flow is substantially separated are produced which compare well with experimental data at low speeds. In addition, three-dimensional steady separation regions and wake vortex patterns are determined. aft) a C D C D f H(t) £ m k m rk M N P Q r f r Subscripts m 0 s k Nomenclature radius as function of time characteristics length of two dimensional unsteady flowfield coefficient of drag coefficient of pitching moment about point [0,0,A*] coefficient of sectional normal force coefficient of normal force coefficient of pressure maximum body diameter drag fineness ratio ( = £/d) step function ( = 0, f < 0, = 1 , body length distance of vrotex from origin = point vortex /3 = freestream value = partial derivatives , f >0) location of vortex born from boundary layer location of vortex born from rear shear layer pitching moment normal force pressure dynamic pressure polar radius body radius vortex core radius boundary-layer variable outer flow evaluated at surface inner flow inner flow forward rear = extremum = stagnation point = separation point = at time t k
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