A Study of Two Dimensional Panel Flutter

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Figure

Figure 23). The sl~iall contribu~on of

Figure 23).

The sl~iall contribu~on of p.64
TABLE U RESULTS OF

TABLE U

RESULTS OF p.90
FIG. 2 - THEORETICAL PANEL THICKNESS REQUIREMENTS TO
FIG. 2 - THEORETICAL PANEL THICKNESS REQUIREMENTS TO p.92
FIG. 3 - SCHEMATIC DIAGRAM OF THE TEST PANEL INSTALLATION IN THE CEILING OF THE TRANSONIC WIND TUNNEL
FIG. 3 - SCHEMATIC DIAGRAM OF THE TEST PANEL INSTALLATION IN THE CEILING OF THE TRANSONIC WIND TUNNEL p.93
FIG. 4 -TYPICAL VELOCITY PROFILES OF THE BOUNDARY LAYER OVER THE TEST PANEL INSTALLATION IN THE WIND TUNNEL CEILING
FIG. 4 -TYPICAL VELOCITY PROFILES OF THE BOUNDARY LAYER OVER THE TEST PANEL INSTALLATION IN THE WIND TUNNEL CEILING p.94
FIG. 5 (a) NODAL LINES FOR PANEL MODE ( 2 ,0 )
FIG. 5 (a) NODAL LINES FOR PANEL MODE ( 2 ,0 ) p.95
FIG. 5 ( b ) .PANEL MODE ( 2, 1 )
FIG. 5 ( b ) .PANEL MODE ( 2, 1 ) p.96
FIG. 5 ( c ) PANEL MODE ( 2 , 2 )
FIG. 5 ( c ) PANEL MODE ( 2 , 2 ) p.96
FIG. 5 ( d 1 PANEL MODE ( 3 , O )
FIG. 5 ( d 1 PANEL MODE ( 3 , O ) p.97
Fig. 6. A typical power spectrum of the test panel response to jet noise Spectral peaks a r e exhibited a t the natural frequencies of the
Fig. 6. A typical power spectrum of the test panel response to jet noise Spectral peaks a r e exhibited a t the natural frequencies of the p.98
Fig. 7a.
Fig. 7a. p.99
Fig. 7b.
Fig. 7b. p.100
Fig. 8.
Fig. 8. p.101
Fig. 9a. Variation of the mean square plate response with time in the non-flutter region.
Fig. 9a. Variation of the mean square plate response with time in the non-flutter region. p.102
FIG. 1 0 - T Y P I C A L VARIATION OF THE MEAN SQUARE RESPONSE OF A TEST PANEL AT THE FLUTTER BOUNDARY
FIG. 1 0 - T Y P I C A L VARIATION OF THE MEAN SQUARE RESPONSE OF A TEST PANEL AT THE FLUTTER BOUNDARY p.103
Fig. 11.
Fig. 11. p.104
Fig. 13. Panel response during flutter.
Fig. 13. Panel response during flutter. p.106
FIG. 14-THE VARIATION WITH MACH NUMBER OF THE FREQUENCIES OF LATERAL VIBRATION OF A TEST PANEL
FIG. 14-THE VARIATION WITH MACH NUMBER OF THE FREQUENCIES OF LATERAL VIBRATION OF A TEST PANEL p.107
FIG. 15- EXPERIMENTAL FLUTTER BOUNDARIES FOR BRASS PANELS EXPOSED TO AN AIRSTREAM WITH SEA LEVEL STAGNATION CONDITIONS
FIG. 15- EXPERIMENTAL FLUTTER BOUNDARIES FOR BRASS PANELS EXPOSED TO AN AIRSTREAM WITH SEA LEVEL STAGNATION CONDITIONS p.108
FIG. I6b-TRANSONIC
FIG. I6b-TRANSONIC p.110
FIG. 17-FLUTTER BOUNDARIES FOR SIMPLY SUPPORTED PANELS
FIG. 17-FLUTTER BOUNDARIES FOR SIMPLY SUPPORTED PANELS p.111
FIG. I9 -VARIATION OF "FIRST MODE " THICKNESS REQUIREMENTS WITH THE STRUCTURAL DAMPING COEFFICIENT g
FIG. I9 -VARIATION OF "FIRST MODE " THICKNESS REQUIREMENTS WITH THE STRUCTURAL DAMPING COEFFICIENT g p.113
FIG. 20-EFFECT
FIG. 20-EFFECT p.114
Fig. 23, Ratio of the eaergy copleribuefora per cycle at flutter orig-king from the rs%atic aarodylnarnic term and the iategral term in the
Fig. 23, Ratio of the eaergy copleribuefora per cycle at flutter orig-king from the rs%atic aarodylnarnic term and the iategral term in the p.117
FIG. 24- COMPARISON OF THE THEORETICAL FLUTTER BOUNDARIES WITH THE EXPERIMENTAL RESULTS
FIG. 24- COMPARISON OF THE THEORETICAL FLUTTER BOUNDARIES WITH THE EXPERIMENTAL RESULTS p.118

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