THREE-DIMENSIONAL BOUNDARY-LAYER METHODS FOR TACTICAL MISSILE CONFIGURATIONS

THE DEVELOPMENT OF TWO DIFFERENT THREE-DIMENSIONAL (3-D) BOUNDARYLAYER COMPUTER CODES AND THE COUPLING OF THESE CODES TO A 3-D SUPERSONIC INVISCID FLOW-FIELD CODE TO ACCURATELY DETERMINE THE SKINFRICTION DRAG FOR MISSILE CONFIGURATIONS THAT MAY HAVE AIR-BREATHING INLETS AND FINS IS PROPOSED. BOTH FINITE-DIFFERENCE AND INTEGRAL SOLUTIONS TO THE 3-D BOUNDARY-LAYER EQUATIONS WILL BE DEVELOPED, INCLUDING THE EFFECTS OF BOUNDARY-LAYER TRANSITION, TURBULENCE, CROSSFLOW SEPARATION, AND SHOCK WAVE-BOUNDARY LAYER INTERACTION. IN ADDITION, THE RESULTING BOUNDARY-LAYER CODES WILL BE COUPLED TO AN EXISTING STATE-OF-THE-ART 3-D INVISCID CODE, NAMELY WITHER SWINT (SUPERSONIC WING, INLET, TAIL), DEVELOPED BY NAVAL SURFACE WEAPONS CENTER, OR CM3DS (CONFORMAL MAPPING 3-DIMENSIONAL SUPERSONIC), DEVELOPED BY SCIENCE APPLICATIONS INTERNATIONAL CORPORATION. IN ADDITION, A DETAILED INVESTIGATION OF THE EXISTING EXPERIMENTAL DATA-BASE FOR SUPER-SONIC FLOWS ABOUTH THREE-DIMENSIONAL GEOMETRIES, WITH PARTICULAR ATTENTION TO CONFIGURATIONS HAVING AIR-BREATHING INLETS AND FINS, WILL BE CARRIED OUT, AND REYNOLDS NUMBER-MACH NUMBER MAPS DEVELOPED FOR COMPARISON WITH FLIGHT CONDITIONS. WHERE DIFFERENCES EXIST, MEANS OF INTERPOLATING AND/OR EXTRAPOLATING THESE DATA TO FLIGHT CONDITIONS WILL BE DEVELOPED, UTILIZING CODE RESULTS AS A GUIDE.