The steady-state and transient effects of simulated heavy rain on the subsonic aerodynamic characteristics of a wing model were determined in the Langley 14- by 22-Foot Subsonic Tunnel. The 1.29 foot chord wing was comprised of a NACA 23015 airfoil and had an aspect ratio of 6.10. Data were obtained while test variables of liquid water content, angle of attack, and trailing edge flap angle were parametrically varied at dynamic pressures of 10, 30, and 50 psf (i.e., Reynolds numbers of .76x10(6), 1.31x10(6), and 1.69x10(6)). The experimental results showed reductions in lift and increases in drag when in the simulated rain environment. Accompanying this was a reduction of the stall angle of attack by approximately 4 deg. The transient aerodynamic performance during transition from dry to wet steady-state conditions varied between a linear and a nonlinear transition.
Steady-State and Transitional Aerodynamic Characteristics of a Wing in Simulated Heavy Rain
1989
95 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Fluid Mechanics , Aerodynamic characteristics , Aerodynamic stalling , Airfoils , Rain , Steady state , Transient response , Wings , Angle of attack , Aspect ratio , Environment simulation , Lift drag ratio , Moisture content , Pressure effects , Reynolds number , Trailing edges , Wind tunnel tests