NASA Technical Reports Server (NASA) · 1977 · 30 citations · 0 references
Open access
EngineeringAerospace EngineeringMechanical EngineeringAerodynamicsAerospace StructuresComputational Fluid DynamicsAerodynamic DesignAerodynamic TestingAirfoil TheoryExperimental AerodynamicsRotorcraft AerodynamicsTransonic AerodynamicsAirfoil AerodynamicsAirfoil DesignFlow Over AirfoilsMach NumberReynolds NumberThickness DistributionTransonic Airfoil AerodynamicsTransonic Airfoils
An investigation was conducted in the Langley 6- by 28-inch transonic tunnel and the 6- by 19-inch transonic tunnel to determine the two-dimensional aerodynamic characteristics of several rotorcraft airfoils at Mach numbers from 0.35 to 0.90. The airfoils differed in thickness, thickness distribution, and camber. The FX69-H-098, the BHC-540, and the NACA 0012 airfoils were investigated in the 6- by 28-inch tunnel at Reynolds numbers (based on chord) from about 4.7 to 9.3 million at the lowest and highest test Mach numbers respectively. The FX69-H-098, the NLR-1, the BHC-540, and the NACA 23012 airfoils were investigated in the 6- by 19-inch tunnel at Reynolds numbers from about 0.9 to 2.2 million at the lowest and highest test Mach numbers respectively.