Method for Rapid Graphical Evaluation of Cooled or Uncooled Turbojet and Turboprop Engine or Component Performance (effects of Variable Specific Heat Included) (1955)
NASA Technical Reports Server (NTRS) · leaf 46
MCA TN 3335 45 to … Figure 10. - Specific thrust for convergent exhaust nozzle. For pressure ratios less than 2, use figure 9 for convergent-divergent exhaust nozzle. (A large working copy of this chart may be obtained by using the request card bovmd In the back of the report.) NACA-Langley - 1-17-55 - 1000
NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
