FREE-FLIGHT MEASUREMENTS OF THE TRANSONIC DRAG CHARACTERISTICS OF LOW-FINENESS-RATIO CYLINDERS INCLUDING STABILIZING PLATES AND FLARES AND VARYING NOSE BLUNTNESS

摘要

Various blunt-nose configurations of low fineness ratio were tested in free flight from Reynolds numbers per foot of 4.0 x 10° to 8.5 x 106 and from Mach numbers of 0.6 to 1.2. The basic configuration was a right circular cylinder of a fineness ratio of 2.0. A single stabilizing plate at the front and at the rear was tested and also a 16.5° conical flare. Various nose radii were tested along with 16.5° truncated-cone nose fairings.nAll stabilizing devices increased the drag coefficient of the right circular cylinder inasmuch as the. projected frontal area was doubled. The conical-flare model, however, only had 30 percent more drag than the cylinder. The truncated-cone nose fairings were more effective than the circular-arc nose fairings in reducing drag coefficient at the test Reynolds numbers and Mach numbers.