Free-Flight Range Tests of Blunted 4-, 4.5- and 5-Caliber Bodies of Revolution with Secant-Ogive, Tangent-Ogive, and Conical Nose Shapes
Abstract
Results of free-flight range tests of spin stabilized, blunted 4-, 4. 5-, and 5-cal bodies of revolution with secant-ogive, tangent-ogive, and conical nose shapes, and cylindrical afterbodies with and without boattails are presented. The tests were conducted over a Mach number range from approximately 1.5 to 3.5 and at simulated altitudes up to 60,000 ft. Measurements indicate that the drag coefficient decreased with increasing nose length and that the secant-ogive nose shape had the minimum drag coefficient. The drag coefficient could be further reduced by the addition of a boattail. Measurements also indicate that the static instability decreased significantly with an increase in the ogive radius of the nose. Nonlinear variations of force and moment coefficients with yaw angle were observed and treated using a cubic analysis.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1971
- Accession Number
- AD0889662
Entities
People
- G. L. Winchenbach
- R. M. Watt
Organizations
- Arnold Engineering Development Complex