An Experimental Study of Attenuation of Shock Waves in Aircraft Fuel Tanks
Abstract
When a full, or partially full, aircraft fuel tank is penetrated by a high velocity projectile, a phenomenon known as hydraulic ram effect, created by the passage of a projectile through the fluid often causes massive damage to the tank. This study was conducted to continue experimental investigation of the attenuation of the hydraulic ram effect through addition of a gas to a fuel-foam mixture. The tests were conducted using two types of projectile (1/2 in. steel spheres and 0.50 caliber ogival projectiles) which were fired into a test tank. The tank was filled first with water and then a water/Pneumacel mixture. Four pressure transducers were located in the back wall of the tank and two pressure transducers were located inside the tank to measure the pressure pulses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1973
- Accession Number
- AD0769930
Entities
People
- John R. Breuninger Jr
Organizations
- Air Force Institute of Technology