Free-flight investigation of the drag of a 60 deg delta-wing configuration with large stores mounted below the indented fuselage at mach numbers between 0.8 and 1.6

Free-flight tests near zero lift were conducted between Mach numbers 0.8 and 1.6 to determine the drag of a 60' delta-wing configuration with large stores under the fuselage.M = 1.0 ness ratios of 8, 10, and 12 and with equal volume were mounted on struts and tested in the region of the fuselage indentation.placement of the stores was held constant.isolated stores also were tested.The fuselage was indented for to cancel only the wing areas.Three finned stores with fine-The vertfcal dis-Small-scale models of the Increasing the store fineness ratio from 8 to 10 to 12 resulted in successive reductions in total drag.Unfavorable interference effects were obtained from each store through the Mach number range except for the fineness-ratio-12 store at the higher supersonic Mach numbers.agreement obtained between the measured pressure drags and those calculated models with stores.The from the supersonic-area-rule theory ranged from good to poor e. e..