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Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow

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Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow ( aerodynamic-design-nasa-rotor-67-non-uniform-inflow )

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Master Thesis Report Literature Review Figure 2.7: Control Volume of aircraft with and without BLI configuration [3] In actual situation, all form of kinetic energy outflow are converted into dissipations downstream of the aircraft. Using this fact, the dissipation term in the power balance equation can be separated into various sources as follows: Ps + Pk = Wh ̇ +(E ̇p +Φvortex)+ + (E ̇w + Φwave) + (Φfuse − Pv,fuse) + (E ̇a,wake + E ̇p,wake + Φwake − Pv,wake) + (E ̇a,jet + E ̇p,jet + Φjet − Pv,jet) Defining the mechanical energy loss as follows: Φ∗ =􏰚E ̇ +􏰚Φ−􏰚PV The power balance equation can be simplified as follows: Ps + Pk = Wh ̇ + (Φ∗)vortex + (Φ∗)wave + (Φ∗)fuse + (Φ∗)wake + (Φ∗)jet (2.7) (2.8) (2.9) Considering that the flight configuration of both system in figure 2.7 is level (therefore, the flight path angle is equal to zero); Wh ̇ = WV∞sinγ = 0 and that no components are moving relative to the control volume, Ps = 0. The power balance equation of a non BLI configuration can then be expressed as shown in equation 2.10: Pk = (Φ∗)vortex + (Φ∗)wave + (Φ∗)fuse + (Φ∗)wake + (Φ∗)jet (2.10) As for the BLI configuration, the net propulsive power is the sum of the mechanical flow power without the jet dissipation, (PK −(Φ∗)jet). The (Φ∗)wake is reduced by a factor, fBLI as a result of the ingested wake by the engine. The remaining dissipation term from the fuselage, wave pressure as well as the vortex source are approximately the same for both the BLI and non BLI concept. The power balance equation of an BLI configuration can be expressed as shown in equation 2.11: Pk − (Φ∗)jet = (1 − fBLI)(Φ∗)wake + (Φ∗)fuse + (Φ∗)vortex + (Φ∗)wave (2.11) 8

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