Accession Number : AD0466300


Title :   TWO-DIMENSIONAL WIND TUNNEL TESTS OF AN H-34 MAIN ROTOR AIRFOIL SECTION


Descriptive Note : Technical rept.


Corporate Author : UNITED TECHNOLOGIES CORP STRATFORD CT SIKORSKY AIRCRAFT DIV


Personal Author(s) : Lizak, Alfred A


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/466300.pdf


Report Date : Sep 1960


Pagination or Media Count : 103


Abstract : Tests were conducted in the two-dimensional channel of the United Aircraft Corporation 8 foot wind tunnel at Mach Numbers from 0.30 to 0.80 to determine the surface pressure distributions on a Sikorsky H-34 main rotor production blade section. Twenty-nine static pressure taps were located on the upper and lower surfaces of the model. In addition three component force and moment measurements, were obtained, along with a limited amount of wake survey drag data. The pressure coefficients are tabulated for each Mach Number and angle of attack. The variation of force and moment coefficient with angle of attack at each Mach Number is also included.


Descriptors :   *ROTOR BLADES(ROTARY WINGS) , AERODYNAMIC CHARACTERISTICS , BLADE AIRFOILS , DISTRIBUTION , DRAG , FORCE(MECHANICS) , MOMENTS , PRESSURE , SUBSONIC CHARACTERISTICS , TWO DIMENSIONAL FLOW , WAKE


Subject Categories : Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE