Flight-Test Temperature Data for an Altair-IIC1 Rocket Motor.
Abstract
Comparison of chamber wall temperatures obtained from flight data and static tests at altitude shows some differences. The flight data indicate maximum chamber wall temperatures of 800 F as compared with maximum temperatures of 400 F for static tests on the chamber wall at simulated altitude. Comparison of static data for a foil wrapped and a nonwrapped chamber indicates foil wrapping causes an increase in temperature from 400 F to 700 F. Flight temperatures are sufficiently high to cause epoxy resin boiloff, charring of the chamber wall, and resultant loss of chamber structural strength.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1965
- Accession Number
- ADA307603
Entities
People
- James L. Rapter
Organizations
- Langley Research Center