AERODYNAMIC CHARACTERISTICS OF MISSILE CONFIGURATIONS WITH WINGS OF LOW ASPECT RATIO FOR VARIOUS COMBINATIONS OF FOREBODIES, AFTERBODIES, AND NOSE SHAPES FOR COMBINED ANGLES OF A_vfACK AND SIDESLIP AT A MACH NUMBER OF 2.01

An investigation has been made in the Langley 4- by 4-foot super-sonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and various nose shapes were determined. Six-component force and mcment data are presented for combined angles of attack and sideslip to about 28 °. No analysis of the data has been made in this report. INTROD_T_N A problem of increasing importance in missile design is the effi-cient utilization of internal stowage space in aircraft. The use of low-aspect-ratio lifting surfaces with small span-diameter ratios would result in more compact missiles occupying materially less volume than the same number of configurations with large-span lifting surfaces. Another problem of missile design is the maneuverability required by the limited scanning angles of the missile seeking equipment. The missile should be capable of large attitude changes with minimum control deflections. A configuration with nonlinear lift and pitching-moment variations such that the values of static margin and lift-curve slope are low near zero angle of attack would satisfy this requirement. i_;: " _ " t)i i • i:;:!i! T iA i k i,_:., j _:,;i _ _fi_< _ ",.......... c]:,