Modification and Additional High Speed Testing in the NASA-Langley 16 Foot Transonic Wind Tunnel of the ADAM Model Developed under AF33(615)-3293 (Knuckle Interference Testing).
LTV AEROSPACE CORP DALLAS TX VOUGHT AERONAUTICS DIV
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The report presents an analysis of data from a high speed wind tunnel test of a powered propulsive wing aircraft concept test Mach numbers ranged from 0.4 to 0.96. The model was tested only with undeflected thrust. The prime purpose of the test was to determine the effects of a large pitch range knuckle on the aerodynamic characteristics recorded in a previous test of the same model in the same wind tunnel a removable, dummy knuckle was used in this test. Secondary purposes of this test were to determine the effects of enlarged fan exit areas, a reshaped flap undersurface and increased fan thrust made possible by the use of a new oil-mist fan bearing lubrication system. Knuckle effects on lift, drag and pitching moments are discussed and documented both thrust included and thrust removed data are presented. The oil mist lubrication system was found to be an excellent means of lubricating and cooling the fan bearings to provide maximum rpm capability. The reshaped flap undersurface was found to cause a favorable change in the model drag rise characteristics. The momentum coefficient is used to correlate the data however, the data from this test indicate the need for a better correlation parameter. Author
- Test Facilities, Equipment and Methods