NASA Technical Reports Server (NASA) · 1974 · 62 citations · 0 references
EngineeringAerospace EngineeringAerodynamicsComputational Fluid DynamicsFluid DynamicsAerodynamic DesignAerodynamic TestingAirfoil TheoryComputational AerodynamicsExperimental AerodynamicsExternal AerodynamicsAerodynamic DragAirfoil AerodynamicsCamber EffectsCurvatureFlow Around AirfoilsFlow Over AirfoilsMach NumberWing Camber
NASA supercritical airfoils feature a flattened upper‑surface mid‑chord and increased trailing‑edge camber, producing distinct aerodynamic behavior that has been examined in wind‑tunnel studies. An analytic method for predicting the aerodynamic characteristics of supercritical airfoils is presented, and flight demonstrations on the F‑8, T‑2C, and F‑111 have validated the approach. The results indicate that the drag‑rise Mach numbers for NASA supercritical airfoils are 0.1 higher than for comparable NACA 6‑series airfoils.
NASA supercritical airfoils are characterized by a substantially reduced curvature of the midcord region of the upper surface together with increased camber near the trailing edge. The basic aerodynamic phenomena associated with the airfoils and representative wind tunnel results are discussed. The results indicate that the drag rise Mach numbers for NASA supercritical airfoils are 0.1 higher than for comparable NACA 6-series airfoils. A recent analytic method for predicting the aerodynamic characteristics of supercritical airfoils is described. The flight demonstration programs of three applications of supercritical airfoils utilizing the F-8, T-2C and F-111 as test beds are summarized.