Pressure data from a number of previous wind tunnel and flight investigations of high speed transport type wings were analyzed with the intent of developing a procedure for extrapolating low Reynolds number data to flight conditions. These analyses produced a correlation of the development of trailing-edge separation resulting from increases in Mach number and/or angle of attack and show that scale effects on this correlated separation development and the resulting shock location changes fall into a regular and apparently universal pattern. Further studies appear warranted to refine the correlation through a detailed consideration of boundary layer characteristics, and to evaluate scale effects on supercritical wings.
Correlation of data related to shock-induced trailing-edge separation and extrapolation to flight Reynolds number
1979-09-01
Report
Keine Angabe
Englisch
Reynolds Number Extrapolation of Transonic Wing Pressure Data Affected by Shock-Induced Separation
SAE Technical Papers | 1986
|Trailing-edge flows at high Reynolds number
AIAA | 1979
Trailing-Edge Flows at High Reynolds Number
AIAA | 1980
|Asymmetric trailing-edge flows at high Reynolds number
AIAA | 1980
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