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By Prof. Dr. Richard Eppler (auth.)

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Extra info for Airfoil Design and Data

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If a positive l! is used, a very small adverse pressure gradient occurs in the main pressure recovery near the trailing edge and the airfoil would be very thin in this region. Therefore, a positive value of KR should be specified to obtain a trailing edge which is thick enough for construcation purposes. 3 was specified for A* =);:* = 4. KR does not yield unusually blunt trailing edges. 0 do not yield unusually blunt trailing edges. Depending on A*, higher The rx-value for the recovery segment Xw < x < same.

The viscous effects in the boundary layer are summarized in Fig. 3. The boundary layer computation must explain and predict the following: a) skin friction and friction drag b) boundary layer separation for laminar and turbulent boundary layers 55 c) boundary layer transition d) laminar separation bubble e) eventually a displacement effect of the boundary layer. Turbulent reattachment Enlargement Turbulent boundary layer layer Separat ion Transition Nonviscous Flow Fig. 2 The Computation of Laminar and Turbulent Boundary Layers Boundary layer computations require by far the largest effort for producing data which the user needs for airfoils.

The most significant and most frequently used mean line has a constant velocity difference between the upper and lower surfaces in the linearized theory for ex = 0°. The fourth digit of the NACA 6-series nomenclature is 10 c Rj ' where c Rj is the design lift coefficient which occurs at approximately ex = 0°. As an example, the NACA 65 3 -618 airfoil is shown in Fig. 12. The velocity distributions are given for ex relative to the x-axis. 5. The analysis method of Chapter 2 shows that further unintended deviations from the design features occur due to the inexact generation of the camber.

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