Airfoil Design and Data by Prof. Dr. Richard Eppler (auth.)

By Prof. Dr. Richard Eppler (auth.)

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1137. 5 oc. 36° v oc. 8~ Oi~i o Fig. 5 1 Airfoil 994 shape and velocity distributions =0° is not decreases with x. 5 Fig. 4 was selected for airfoil 990. This can always be corrected by changing tl and 11. tendency However, the amount of the change depends on the design and the other parameters of the recovery function. 5. This is demonstrated in Fig. 0. 5). 1) and x(cp). With regard to the airfoil thickness, if trailing edge iteration modes 1 to 3 or 7 to 9 are used, the prespecified total amount of recovery influences the airfoil thickness strongly, but it does not fix it uniquely.

This will be discussed in more detail in Chapter 5. 5 ~ 01 o . ---1 Fig. 53%~ o Fig. 5 IX x/c *-values over segments 52 and 53 37 Incidentally, iteration modes 7 to 9 are not used very often in practice. They have been developed for the special design problems of hydrofoils, where cavitation is critical [6], [7]. In most other applications, the pressure recovery on one surface is of interest for those angles of attack which are fixed relative to the a": of the same surface. Then the a": of I I the recovery sections must be included in the iteration, which is true for modes 1 to 3.

Of course, "5:* are reqUired to be integer numbers. On the specified to lie halfway between points (for example, as this yields smoother velocity distributions. The airfoil to be designed is specified in two different line types, the TRA1- and TRA2-lines. 7. TRA1-line: This line contains the arc limits v. and the Columns 1 - I 4, the line type (in this case, TRAll. Columns 5 - 6, Columns 7 - NUPA and NUPE are neglected. 2, and NUPUl. I The input for the arc limit If more than 7 arcs at the leading edge, which is computed, must be \l iL are to be introduced, more TRA1-lines must follow.

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