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TABLE OF CONTENTS
Page No.
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . iii
Section I . . . . Charteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
A. Background . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
B. Description of the Proposed Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
C. Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
Section I I. . . . USAF Research and Development Status . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
A.Principal Problem Areas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
B. Present Development Status . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
LIST OF ILLUSTRATIONS
Figure 1 . . . . Three-view General Arrangement of Proposed Multi-engine Research Aircraft . . . 2
Figure 2 . . . . Cut Away of Research Aircraft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
Figure 3 . . . . Three-view General Arrangement of Research Aircraft . . . . . . . . . . . . . . . . . . . . . 5
Figure 4 . . . . Section Cutaway of Research Aircraft. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6
Figure 5 . . . . Ground Cushion Effect . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
Figure 6 . . . . Airflow Into Intake During Take-off and Landing . . . . . . . . . . . . . . . . . . . . . . . . . 11
Figure 7 . . . . Section of Airflow Pattern for Take -off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
Figure 8 . . . . Typical Section of Exhaustor Duct Showing Take-off Gas Flow . . . . . . . . . . . . . . 13
Figure 9 . . . . Section Through Rear of Aircraft at Supersonic Speed . . . . . . . . . . . . . . . . . . . . . 14
Figure 10 . . . .Typical Cross-Section Through Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15
Figure 11 . . . .Through Flow at Low Forward Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
Figure 12 . . . .Cross-Section Showing Bearing Airflow . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
Figure 13 . . . .Perspective View Showing True Path of Bearing Air . . . . . . . . . . . . . . . . . . . . . . 19
Figure 14 . . . .Exhaust Jet Angles at Low Forward Speed. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
Figure 15 . . . .Conanda Effect: High Aspect Ratio Jet Bending. . . . . . . . . . . . . . . . . . . . . . . . . . 21
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TABLE OF CONTENTS (Cont)
Page No.
Table I . . . . Physical Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
Table II . . . .Weight Breakdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
Table III. . . .Contractor Estimated Performance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
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