Accession Number : AD0012310


Title :   APPLICATION OF CIRCULATION CONTROL TO AN AIRPLANE OF MILITARY LIAISON TYPE


Corporate Author : CESSNA AIRCRAFT CO WICHITA KS


Personal Author(s) : Petroff, Alex ; Fisher, Jack W ; Blosser, Earl G


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/012310.pdf


Report Date : May 1953


Pagination or Media Count : 14


Abstract : Rerigging the aileron droop system reduced the lateral unbalance and improved the stall of the model 309A-309C airplane. The stall was brought to normal by changing the horizontal tail incidence from -3 deg to -1.25 deg. The breakdown, climb, and approach speeds were determined for conditions with the boundary-layer-control system on and off; the elevator area was increased by a 3-in. Al strip added to the trailing edge. Efforts will be directed toward developing the demonstrator airplane rather than the research airplane, because of difficulties envisaged in the installation of a 2-cycle gasoline engine in the research plane. The model 319A demonstrator plane will consist of an L-19 fueslage, a thicker wing to accommodate the fans, a 225-hp Continental engine, and a Hartzell constant-speed propeller. Hydraulic motors driven by a hydraulic pump belted to the engine were considered the most promising source of motive power for the 2 axial fans from the standpoint of mechanical efficiency and availability. Calculations indicated that the hydraulic system will afford a 20% decrease in take-off distance over a 50-ft obstacle.


Descriptors :   *AIRCRAFT DESIGN , *AERODYNAMIC CHARACTERISTICS , TAIL ASSEMBLIES , EFFICIENCY , TAKEOFF , RANGE(DISTANCE) , HYDRAULICS , WINGS , MOTORS , RESEARCH AIRCRAFT , HYDRAULIC EQUIPMENT , HYDRAULIC PRESSURE PUMPS , UTILITY AIRCRAFT , AILERONS , TRAILING EDGES , HORIZONTAL STABILIZERS , ELEVATORS , DEMONSTRATIONS , VELOCITY , MECHANICAL PROPERTIES


Subject Categories : Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE