The Design of Constant-volume Missile Fuselages Having Minimum Drag at Supersonic Speeds
The factors influencing the design of missile fuselages are discussed in relation to the problem of obtaining an optimum design from the drag standpoint. On the basis of the factors and assumptions given, a method is developed for determining the fineness ratio that results in minimum drag for a constant-volume fuselage flying at a fixed angle of attack and Mach number. Using drag data for the attitude of zero angle of attack at Mach numbers between 1.5 and 5, numerical values of optimum fineness ratio are presented for the case of a practical, axially-symmetric fuselage whose shape consists of a conical nose of fixed proportions attached to a cylindrical afterbody. Procedures are indicated for the extension of the results of the study to specific designs of the subject or other geometrical configurations.
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absolute magnitudes aerodynamic altitude analysis angle of attack base area base drag coefficient boundary layer i.e. calculated Combining Eqs compressible boundary layer compressible flow regimes CONICAL NOSE ANGLES constant-volume cylindrical afterbody d3 is proportional decrease defined as drag)/2 design Mach number df/dA drag at constant Drag force drag Is Incurred drag penalty drag question drag standpoint due to boattail errors involved exact values frontal area fuselage drag fuselage geometry FUSELAGES HAVING VARIOUS geometrical configuration iteration LU LU Maoh minimum drag missile designed N.A.C.A. standard number and angle NUMBER FOR CONSTANT obtain ogive opt opt optimum design optimum fineness ratio present study procedure range referred to frontal relation for a/a Reynolds number Ropt sin2 standard atmosphere SUPERSONIC SPEEDS Alan tactical requirements total drag total fuselage volume value of b/d)2 VOLUME MISSILE FUSELAGES wave drag wetted area zero angle