NASA STI Repository (National Aeronautics and Space Administration) · 1978 · 12 citations · 4 references
Open access
EngineeringAerospace EngineeringAerodynamicsAerospace StructuresFlow VisualizationAerodynamic DesignAerodynamic TestingExperimental AerodynamicsExternal AerodynamicsLow-speed AerodynamicsWing AerodynamicsAngle Of AttackAngle Of Attack EffectsAspect Ratio EffectsLeading-edge DynamicsReynolds NumberReynolds Number EffectsStatic Force AnalysisWing Aspect Ratio Effects
Static force tests were conducted in the Langley V/STOL tunnel at a Reynolds number (based on the mean aerodynamic chord) of about 2.0 x 10 to the 6th power for an angle-of-attack range from about - 10 deg to 17 deg and angles of sideslip of 0 and + or - 5 deg. Limited flow visualization studies were also conducted in order to provide a qualitative assessment of leading-edge upwash characteristics.
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Albert L Braslow, E. C. Knox · University of North Texas Digital Library (University of North Texas) · 1958 · 224 citations · Full text