Thesis

Recommendations

Info

Side View of the Anechoic Facility 8.255 Upper segment Test Section Kevlar acoustic windows 2.44 Lower Segment 6.096 Door Platform Kevlar over perforate floor/ceiling panels and 0.457 m wedges Suction-Side Chamber Pressure-Side Chamber Figure 2-5. Side View of the Virginia Tech Anechoic Facility looking downstream. All dimensions in meters 33
4.216 2.75 Door Suction-Side Chamber Kevlar acoustic window From Contraction Test Section Kevlar over perforate floor/ceiling panels To Diffuser 1.854 B Foam transition B Pressure-Side Chamber Door 1.016 5.588 Figure 2-6. Top View of the Virginia Tech Anechoic Facility. All dimensions in meters 34
Page 1 and 2: Aerodynamics and Acoustics of the V
Page 3 and 4: Aerodynamic measurements with the N
Page 5 and 6: TABLE OF CONTENTS ABSTRACT ii ACKNO
Page 7 and 8: LIST OF SYMBOLS, TABLES AND FIGURES
Page 9 and 10: List of Figures Chapter 2 2.1 Plan
Page 11 and 12: Chapter 3 3.1 Background Noise Leve
Page 13 and 14: 4.9 Complete diagram of all of the
Page 15 and 16: 4.42 Comparison of the measured to
Page 17 and 18: effective angle of attack (top) and
Page 19 and 20: primary types of tunnels; a closed
Page 21 and 22: Another anechoic chamber that was d
Page 23 and 24: 3. To determine the interference co
Page 25 and 26: Flow through the empty hard wall te
Page 27 and 28: facility. The following sections de
Page 29 and 30: measuring 1.016 m wide and 2.235 m
Page 31 and 32: absolute origin was located on the
Page 33 and 34: located near the mid span, location
Page 35 and 36: will be equal since both probes are
Page 37 and 38: test section inlet and exit to dete
Page 39 and 40: minimize an interference effects. W
Page 41 and 42: the test section window (figure 2-3
Page 43 and 44: Hatch Side Opposite Side x/c z/c x/
Page 45 and 46: Suction Side Pressure Side x/c x (i
Page 47 and 48: Figure 2-2. Photograph showing the
Page 49: 0.04 0.03 Hard Wall Test Section Pr
Page 53 and 54: 5.13 m 1.83 m Acoustic Absorbers on
Page 55 and 56: Tensioned Kevlar covering steel per
Page 57 and 58: 2.75 1.473 0.33 0.933 1.054 2.565 D
Page 59 and 60: Figure 2-14. Transition wedges that
Page 61 and 62: Upper transition wedges removed flo
Page 63 and 64: Figure 2-18. Section A-A from Figur
Page 65 and 66: Starboard Side Window Y Z- positive
Page 67 and 68: Figure 2-22. NACA 0012 Model mounte
Page 69 and 70: DU97-W300 Airfoil Model Coordinates
Page 71 and 72: Figure 2-26. Photograph of the stab
Page 73 and 74: Figure 2-28. Boundary layer measure
Page 75 and 76: 0.381 0.05 0.279 0.050 0.102 Figure
Page 77 and 78: 0.03 0.02 Hard Wall Probe Calibrati
Page 79 and 80: 5 Pitot static probes Aluminum moun
Page 81 and 82: Figure 2-36. Wall deflection measur
Page 83 and 84: Figure 2-38. Out of Flow microphone
Page 85 and 86: pressure levels measured in the pro
Page 87 and 88: The boundary layer thickness values
Page 89 and 90: figure the negative static pressure
Page 91 and 92: tunnel speed was increased to a nom
Page 93 and 94: Location Number Port Starboard Cond
Page 95 and 96: 100 Kevlar wall, 1/8-inch Mic, Midd
Page 97 and 98: Suction Side flow 1 10 To Diffuser
Page 99 and 100: Boundary Layer Thickness Distributi
Page 101 and 102:
5 0.610 m NACA 0015 with Lift Inter
Page 103 and 104:
0.16 Boundary Layer Thickness Distr
Page 105 and 106:
0.08 0.06 Kevlar Window Shape on St
Page 107 and 108:
Deflection,m, and CPS 0.2 0.1 0 -0.
Page 109 and 110:
4. RESULTS OF 2007 FINAL CALIBRATIO
Page 111 and 112:
treatment was in addition to the wa
Page 113 and 114:
length, and lined around the circum
Page 115 and 116:
RPM, and thus the overall drag on t
Page 117 and 118:
These plots exclude the 10 m/s spec
Page 119 and 120:
4.4.1 Experimental Approach During
Page 121 and 122:
plots have the chord wise distance
Page 123 and 124:
This confirmed that the Kevlar was
Page 125 and 126:
thickness were computed for a nomin
Page 127 and 128:
For the empty test section the maxi
Page 129 and 130:
measurement. Figure 4-58 has a comp
Page 131 and 132:
positive static pressure coefficien
Page 133 and 134:
(2006) for one example) and the ind
Page 135 and 136:
locations. While the power rule pla
Page 137 and 138:
imposed by the airfoil may also be
Page 139 and 140:
measured) for the 0.9144 m chord NA
Page 141 and 142:
Stability Tunnel Description Power
Page 143 and 144:
Location X Location (m) Velocity (m
Page 145 and 146:
100 80 60 Hard Wall Baseline, 1/8-i
Page 147 and 148:
Settling Chamber, Fan and Completed
Page 149 and 150:
10 8 Original Vane Shape Vane shape
Page 151 and 152:
Completed Large Wall Between 3rd an
Page 153 and 154:
100 Completed Treatment at 10.83 m/
Page 155 and 156:
Page 157 and 158:
Page 159 and 160:
Page 161 and 162:
Upper Anechoic Chamber elliptic aco
Page 163 and 164:
Model installed and removed through
Page 165 and 166:
Steel Panel Cut Outs Kevlar coverin
Page 167 and 168:
Figure 4-24. Photograph showing the
Page 169 and 170:
100 80 Anechoic Configuration with
Page 171 and 172:
100 90 80 In Flow Noise Comparison,
Page 173 and 174:
f = 331 f f = 22 f f = 8 f f f f 10
Page 175 and 176:
20 10 0 2007 Anechoic Configuration
Page 177 and 178:
Narrow band SPL Anechoic Configurat
Page 179 and 180:
0.5 NACA0012, Re= 1448757.67, α ge
Page 181 and 182:
0.5 NACA0012, Re= 3078660.50, α ge
Page 183 and 184:
5 4 NACA0012, Re= 1527936.46, α ge
Page 185 and 186:
1.5 DU96, Re=1580000, α geom =3.8
Page 187 and 188:
1.5 1 B1-18, Re=2940000, α geom =3
Page 189 and 190:
Empty Test Section Port Window Boun
Page 191 and 192:
Ceiling Thickness = 107 mm Port Sid
Page 193 and 194:
Thickness of the Boundary Layer, m
Page 195 and 196:
NACA 0012 at 8 o Effective AOA Port
Page 197 and 198:
y-y o , cm 150 100 50 Starboard Sid
Page 199 and 200:
Starboard Side Window at 30 m/s, NA
Page 201 and 202:
Deflection, cm 10 5 0 -5 Suction Wi
Page 203 and 204:
1 8 0 1 6 0 P r e s s u r e W i n d
Page 205 and 206:
y-y o , cm 150 100 50 Suction Windo
Page 207 and 208:
0.2 0.15 0.1 Conditions on the pres
Page 209 and 210:
Click on plot to start streamline,
Page 211 and 212:
Pressure Window Midheight at 30 m/s
Page 213 and 214:
0.2 0.15 0.1 Conditions on the pres
Page 215 and 216:
Click on plot to start streamline,
Page 217 and 218:
Cumulative mass flux through the wi
Page 219 and 220:
Cumulative mass flux through the wi
Page 221 and 222:
5. CONCLUSIONS The acoustic treatme
Page 223 and 224:
overall levels with the completed f
Page 225 and 226:
REFERENCES 1. Brooks, T. F., Pope,
Page 227:
21. Taylor, G., “Fluid Flow in Re
show all

Thesis

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?