Drag of rectangular planform cavity in a flat plate with a turbulent boundary layer for Mach numbers up to 3. Part I: Closed flow
ESDU 00006 develops a method for predicting the drag where the cavity length is large compared to the depth and the shear flow enters the cavity and attaches to the floor before separating to pass over the rear wall with a stagnation point near the top of the wall (i.e. closed flow). A family of curves suggests an upper limit of cavity depth to length ratio for closed flow in terms of free-stream Mach number and cavity width to length or width to height ratio. In supersonic flow it is possible for vortices to form as the shear flow spills over the side edges of the cavity and their impingement on the rear wall gives rise to an increase in drag for which an estimation method is also provided. Tables give the ranges of parameters covered in the construction of the method. The prediction of the ratio of the drag coefficient, based on floor area, to the local skin friction coefficient at the cavity mid-length station (in the absence of the cavity) is assessed to be within 1 for low-speed flow (Mach number less than 0.1) and to within 2 for high-speed flow (Mach number between 0.5 and 3). Worked examples illustrate the use of the method. A companion ESDU document, ESDU 00007, deals with other types of cavity flow, known as transitional and open. The third Item in the series, ESDU 10016, deals with the effect on cavity drag of a pair of doors open at 90°, including the effects of three different treatments of the door leading and trailing edges.
Software for the method is provided as ESDUpac A1607 and also with an interface as Toolbox 16007.
|Data Item ESDU 00006|
|Toolbox 16007 Run||
This program is only available to subscribers.
The graphs listed below are available only to subscribers.
|Figure 1||Boundaries for closed flow (closed flow likely below each curve)|
|Figure 2||Cavity width factor, F|
|Figure 3||Value of a0|
|Figure 4||Cavity width factor, G|
|Figure 5||Value of b0|
|Figure 6||Mach number factor on a0|
|Figure 7||Mach number factor on b0|
|Figure 8||Mach number factor on arw0|
|Figure 9||Mach number factor on brw0|
|Figure 10||Factor on CDrw/Cfm to give drag due to side-edge vortices|
|Figure 11||Exponent in Equation (4.25) for Cfm|
|Figure 12||Mach number factors for Cfm|
|Figure 13||Local skin friction coefficient on a flat plate|
|Figure 14||Boundary layer thickness on a flat plate|