a wing-body shape The HoW = 1.225kg/m³) conditions in the test section are standard sea-level properties (p with a velocity of 100 m/s. The wing area and chord are 1.5 m² and 0.45 m, respectively. Using the wind tunnel force and moment-measuring balance, the moment about the center of gravity when the lift is zero is found to be -12.4 N m. When the model is pitched to another angle of attack, the lift and moment about the center of gravity are measured to be 3675 N and 20.67 N m, respectively. Calculate the value of the moment coefficient about the aerodynamic center and the location of the aerodynamic center.
a wing-body shape The HoW = 1.225kg/m³) conditions in the test section are standard sea-level properties (p with a velocity of 100 m/s. The wing area and chord are 1.5 m² and 0.45 m, respectively. Using the wind tunnel force and moment-measuring balance, the moment about the center of gravity when the lift is zero is found to be -12.4 N m. When the model is pitched to another angle of attack, the lift and moment about the center of gravity are measured to be 3675 N and 20.67 N m, respectively. Calculate the value of the moment coefficient about the aerodynamic center and the location of the aerodynamic center.
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Consider a model of a wing-body shape mounted in a wind-tunnel. The flow
conditions in the test section are standard sea-level properties (p 1.225kg/m³)
with a velocity of 100 m/s. The wing area and chord are 1.5 m² and 0.45 m,
respectively. Using the wind tunnel force and moment-measuring balance, the
moment about the center of gravity when the lift is zero is found to be -12.4 N m.
When the model is pitched to another angle of attack, the lift and moment about the
center of gravity are measured to be 3675 N and 20.67 N m, respectively. Calculate
the value of the moment coefficient about the aerodynamic center and the location
of the aerodynamic center.
Transcribed Image Text:Geometric Data:
Wing area, S = 1.5 ft² (0.139 m²), Wing mean aerodynamic chord, ☎ = 6.145 in (15.61 cm)
1,= 15.29 in (38.84 cm),Tail area, S,= 0.368 ft² (0.0342 m²)
Aerodynamic Data: Awb = 0.077/deg., at=0.064/deg., &o = 0.72 º
2
0.018, h=0.25, p = 2.377x10-³ slugs/ft³ (1.225 kg/m³)
de
θα
=
0.3, C,
macwb
=
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