Report

3/32-inch diameter Airfoil AIRPLANE WING Angle of attack approximately the N. A. C. A. axis Bernoulli's equation Brazier-head rivets Cdomin chord line Civil Aeronautics Authority compressible flow computed DETERMINATION OF PROFILE downstream drag coefficient drag equation DRAG OF AIRPLANE experimental F₁ feet FLIGHT AT HIGH forward 23 percent free stream heat at constant HIGH REYNOLDS NUMBERS Jones laminar to turbulent LANGLEY FIELD LANGLEY MEMORIAL AERONAUTICAL lap joints measurement plane Measurements to determine MEMORIAL AERONAUTICAL LABORATORY Navy P₁ P₁-Po p₁₁dy panel percent chord FIGURE Pi Pi-Po pitot Pitot Tube Pressure Distribution profile-drag coefficient ratio Reynolds Number range Rough smooth wing specific heat speed stagnation point static pressure static tube stream tube Stream velocity surface irregularities survey plane SYMBOLS total pressure trailing edge transition from laminar transition point true N. A. C. A. turbulent boundary layer upper surface variable-density tunnel velocity distributions wake surveys WING IN FLIGHT Ρι