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Tham khảo tài liệu 'aero-acoustic test programs_4', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Simpo PDF Merge and Split Unregistered Version - http www.simpopdf.com high ưaỉacíCY to J ft ataw Floor prajflit Inn d d 41 r dead í Ir d d SECTION A-A rtnl rẹed I locking iJcwni tri am h igti vsìũĩ.iĩf ar u 5haiJ Ll bulk flow f1 1 d ro tat lend I Ivy tab irnig e b projection n I if ar imiij Figure 16 Cherry Paine Engine Test Cell Internal Flow Patterns with the Pegasus Engine Simpo PDF Merge and Split Unregistered Version - http www.simpopdf.com Section 8 AUGMENTER WALL TEMPERATURE 8.1 Wall Temperature Measurement. For definitions of the terms for equations below refer to Table 1. Measurements of augmenter wall temperature were made in all of the postconstruction facility checkouts reported herein 1 3 8 9 . In addition measurements of augmenter wall temperature were made during the model test programs reported in References 3 14 and 15 . In some cases the augmenter wall temperature data have been reduced to a wall temperature parameter where __ _ wall - anibient EQUATION a 1 Tant lent Measured wall temperatures are plotted versus axial position in the augmenter in Figures 17 18 and 19 for aligned engines or aircraft. Figures 17 and 18 present such data for aligned aircraft and engine cases where the exhaust centerlines were aligned with and nearly contiguous with the augmenter centerline. As a good first approximation the maximum augmenter wall temperature in such cases equals the mixed exhaust temperature where 8.1.1 Wall Temperature with Outward-Splayed Exhaust. Figure 19 contains data for aligned aircraft where the exhaust centerlines were splayed outward and located a significant lateral distance from the augmenter centerline A-6 F-14A and S-3A . In addition Figure 19 contains a projected wall temperature distribution for the F-14A in a Miramar type hush-house based on the model tests 3 . The projection based upon the model tests is quite accurate. EQUATION T ị - 1Ũ2Ũ fj TVill P I aax projected max me as 8.1.2 Wall Temperature with Aircraft Misalignment.
