Accession Number:

ADA056795

Title:

Improved Transonic Nose Drag Estimates for the NSWC Missile Aerodynamic Computer Program

Descriptive Note:

Technical rept. 4 Mar-4 Oct 1977

Corporate Author:

NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CA

Personal Author(s):

• Chaussee, Denny S.

Report Date:

1978-04-01

Pagination or Media Count:

70.0

Abstract:

An axisymmetric implicit unsteady Euler equation solver has been applied to the transonic flow past sphere-ogive-cylinder bodies. This paper documents this method and shows results that were obtained for the full range of transonic Mach numbers, 0.7 or M at infinity or 1.2. The present numerical results are compared to the experiments of Hsieh for M at infinity 0.7, 0.95, 1.0, 1.05, 1.1 flow over hemisphere cylinders. A rather extensive parametric study of sphere-ogive-cylinders was performed over the transonic Mach number range. Nose pressure drag values were calculated and are presented for varying nose radii, 0. to 1.0, varying nose length, 1.0 to 10.0 and varying Mach numbers, 0.7 to 1.2, where all geometric quantities are normalized with respect to the maximum body radius. These results have been included in the NSWC Missile Aerodynamic Computer program to improve transonic nose drag estimates.

Descriptors:

• *AERODYNAMIC DRAG
• *ROCKET NOSES
• *TRANSONIC FLOW
• COMPUTATIONS
• COMPUTER PROGRAMMING
• CONFIGURATIONS
• CYLINDRICAL BODIES
• GUIDED MISSILES
• INVISCID FLOW
• MACH NUMBER
• MACHINE CODING
• NONUNIFORM FLOW
• OGIVES
• SPHERES
• STAGNATION POINT

Subject Categories:

• Guided Missiles
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE