Wall Temperature/Engine Nozzle Distance Correlation

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Figure 19. Augmented Wall Temperature Distribution for Various Facilities Showing the Effect of Significant Engine Centerline Lateral Offset

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Figure 20 Augmented Sidewall Temperature Distribution for F-14A Operation with One Enginein A/B

F-14A operation. The reduction appears to be due to increased augmentation

with the flared augmenter inlet applied at Patuxent River. The results of

F-14A misalignment tests run in Miramar Hush-House No. 2 and reported in

Reference [6] and those run at Patuxent River are summarized in Figure 20.

This shows the rapid increase in maximum augmenter wall temperature with

aircraft misalignment. Figure 20 further shows the beneficial effect of the

flared augmenter inlet on wall temperatures in the Patuxent River hush-house.

8.1.3

Wall Temperature/Engine Nozzle Distance Correlation. Figures 21 and

22 represent an attempt to relate maximum augmenter wall temperature with the

distance from the engine nozzle exit to the impingement point. In Figure 21,

maximum wall temperature parameter,T+P+max,,, is plotted versus the distance

from the nozzle exit to the nondimensionalized location of maximum wall

temperature within the augmenter (this basically portrays the effect of jet

mixing). Figure 22 presents the relationship between hot spot location and

the point at which the projected nozzle centerline intersects the augmenter

wall. Figures 21 and 22 are particularly useful in cases where the nozzle

centerline is canted toward the augmenter wall or where the nozzle centerline

is offset significantly from the augmenter centerline. Even so, Figures 21

and 22 do not account for effects on pumping, such as those derived from the

application of a flared augmenter inlet to the Patuxent River hush-house.