Davidson, Harold William (1951) Lift increase obtained with boundary layer suction on a 10% double wedge airfoil with a 20% chord leading and trailing edge flaps. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-03192009-110707
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In this investigation a study was made of the effects of boundary layer control on a 10% thick, double-wedge airfoil located between endplates. In particular, the study centered around a "high-lift" investigation in order to obtain an optimum configuration for the specific airfoil. The double-wedge airfoil was used since: 1) it is a "high speed" airfoil, and 2) it has poor maximum lift and stalling characteristics.
The model used was equipped with a nose flap and a slotted trailing edge flap, both of 20% wing chord, and two suction slots, one aft of the nose flap (20% chord) and the other at the 70% wing chord. Five suction quantities were used on all possible configuration combinations. The maximum lift coefficient obtained was [...] = 2.149 at an angle of attack of 21° and a suction quantity equal to C[subscript Q] = 0.0071.* For this particular configuration, the approximate value of the horsepower required to supply the necessary suction quantity was determined. In addition to the force and moment tests, tuft studies of flow of the "optimum" configurations were made and reported.
* Configuration: Nose flap deflected 30°; trailing edge flap deflected 30°; slot [...](forward slot)
|Item Type:||Thesis (Engineer's thesis)|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 January 1951|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||19 Mar 2009|
|Last Modified:||26 Dec 2012 02:34|
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