Computation of Transonic Flow about Lifting Wing-Cylinder Combinations

Studies in Transonic Aerodynamic Interference.

“…(6~1~) 6 2 , which is consistent w i t h the f a c t tha t E quati on (48) i s a second order accura te approx ima tion.…”

“…This simp le treatment brings out clearly the difference between Equations ( 5 ) and ( 6 ) and Equations ( 7 ) and ( 8 ) in simulating oblique shocks (7) and (8) Derived from -----P e rtu r b~ILi on Equations (5) and ( …”

“…If the boundary conditions are such that a vertical shock is oblique to the free s tream , the shock posi tion and intensity could be sig n i f i c a n t l y d i f f e r e n t depending on whether Equation s ( 5 ) and ( 6 ) or Equation s ( 7 ) and ( 8 ) wet-e used for the simulation . For example , consider the special c ase where v 9 = -2u., tanO , which exists when the component of the perturbatioft velocity parallel to the shock is zero , which is the condition for simple sweep theory .…”

“…The second form is the usual classical tran sonic equation (CTE) derived from Equation s ( 5 ) and ( 6 ) by considering the special behavior of the fl u i d flow when the local velocity is close to the speed of sound :…”

Unsteady transonic flow simulation on a full-span-wing-body configuration

“…At 90 deg median angle (body symmetry line), the present results are compared with computations based on the classical steady TSD equation. 15 The comparisons are favorable. In Fig.…”