Browse TRAIL Inventories

Test of NACA 66,2-116, a =0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Wind tunnel investigation of control surface characteristics.12 - Various cover-plate alinements on the NACA 0015 airfoil with a 30 percent chord flap and large sealed internal balance

Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory

The NACA balanced-diaphragm dynamometer-torque indicator

Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modification of aileron nose and adjacent airfoil contour

Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles

Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds

Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section.Transonic-bump method

Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925

Investigation of the NACA 4-(4)(06)-04 two-blade propeller at forward Mach numbers to 0.925

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section.Transonic-bump method


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