AN EXPERIMENTAL INVESTIGATION OF TWO METHODS FOR REDUCING TRANSONIC DRAG OF SWEPT-WING AND BODY COMBINATIONS

摘要

The results of these tests indicated that at small angles of attack large variations of downwash angle with angle of attack occurred at the test tail location, similar to those reported in other tests of low-aspectratio wings having tails located in the wing-chord plane. The drag-risewith-lift factor for the wing was found to decrease generally with increasing Mach number, or perhaps more significantly, with simultaneously increasing Reynolds number through the transonic Mach number range covered by the tests. The dominant influence of Reynolds number was further suggested by a similarity noted between the variations with Reynolds number of the drag-rise-with-lift factor for a family of triangular wings and the variations with Reynolds number of the pressure distribution over swept circular cylinders. The experimental increase in minimum drag for the complete model through the transonic Mach number range was closely predicted by use of available methods.