Investigation of Nose Bluntness and Angle of Attack Effects on Slender Bodies in Viscous Hypersonic Flows

By: Nasa, National Aeronautics and Space Adm

Hypersonic flows over cones and straight biconic configurations are calculated for a wide range of free stream conditions in which the gas behind the shock is treated as perfect. Effect of angle of attack and nose bluntness on these slender cones in air is studied extensively. The numerical procedures are based on the solution of complete Navier-Stokes equations at the nose section and parabolized Navier-Stokes equations further downstream. The flow field variables and surface quantities show significant differences when the angle of attack and nose bluntness are varied. The complete flow field is thoroughly analyzed with respect to velocity, temperature, pressure, and entropy profiles. The post shock flow field is studied in detail from the contour plots of Mach number, density, pressure, and temperature. The effect of nose bluntness for slender cones persists as far as 200 nose radii downstream. Sehgal, A. K. and Tiwari, S. N. and Singh, D. J. Unspecified Center ANGLE OF ATTACK; BLUNT BODIES; FLOW DISTRIBUTION; HYPERSONIC FLOW; NOSE CONES; SLENDER CONES; VISCOUS FLOW; AERODYNAMIC CONFIGURATIONS; AIR FLOW; ENTROPY; FLOW VELOCITY; FREE FLOW; MACH NUMBER; NAVIER-STOKES EQUATION; PRESSURE EFFECTS; TEMPERATURE EFFECTS; TEMPERATURE PROFILES...

• Format: Paperback
• Language: English
• ISBN: 1731270801
• ISBN13: 9781731270801
• Release Date: January 1
• Publisher: Independently Published
• Length: 126 Pages
• Weight: 0.68 lbs.
• Dimensions: 0.3" x 8.5" x 11.0"