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Wind-tunnel investigation of two airfoils with 25-percent-chord Gwinn and plain flaps

Description: Aerodynamic force tests of an NACA 23018 airfoil with a Gwinn flap having a chord 25 percent of the overall chord and of an NACA 23015 airfoil with a plain flap having a 25-percent chord were conducted to determine the relative merits of the Gwinn and the plain flaps. The tests indicated that, based on speed-range ratios, the plain flap was more effective than the Gwinn flap. At small flap deflections, the plain flap had lower drag coefficients at lift-coefficient values less than 0.70. For lif… more
Date: May 1940
Creator: Ames, Milton B., Jr.
Item Type: Refine your search to only Report
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Wind-Tunnel Tests and Analysis of Two 10-Foot-Diameter Six-Blade Dual-Rotating Tractor Propeller Differing in Pitch Distribution

Description: Report presenting an investigation to determine the efficiency at low tip speeds of two 10-foot-diameter six-blade dual-rotating propellers differing only in pitch distribution. Propeller forces were determined from wind tunnel testing and by using an analytical method using two-dimensional airfoil section data. Results regarding propeller characteristics, analysis of energy losses, and design considerations are provided.
Date: June 1948
Creator: Gilman, Jean, Jr.
Item Type: Refine your search to only Report
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Wind tunnel tests of an NACA 23021 airfoil equipped with a slotted extensible and a plain extensible flap

Description: "An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 airfoil equipped with two arrangements of a completely extended 15 percent chord extensible flap. One of the flaps had a faired juncture, without a gap; the other was provided with a slot between the trailing edge of the airfoil and the nose of the flap. The results showed that the basic airfoil gave the lowest profile-drag coefficients over the low lift range, the airfoil with the plain extensible… more
Date: November 1940
Creator: Swanson, Robert S. & Harris, Thomas A.
Item Type: Refine your search to only Report
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Wing plan forms for high-speed flight

Description: Report presenting an analysis which indicates that for aerodynamic efficiency, wings designed for flight at supersonic speeds should be swept back at an angle greater than Mach angle and the angle of sweepback should be such that the component of velocity normal to the leading edge is less than the critical speed of the airfoil sections. This principle can also be applied to wings designed for subsonic speeds.
Date: March 1946
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
open access

Wing Pressure-Distribution Measurements Up to 0.866 Mach Number in Flight on a Jet-Propelled Airplane

Description: Report presenting flight testing to determine scale and compressibility effects on the pressure distributions over a wing with an NACA low-drag profile. No compressibility effects on spanwise wing loading were noted below Mach number 0.75, but above that number, an inboard lateral shift of load occurred that is primarily due to the upfloating of the ailerons.
Date: March 1947
Creator: Brown, Harvey H. & Clousing, Lawrence A.
Item Type: Refine your search to only Report
open access

Wing-tunnel investigation of effects of forward movements of transition on section characteristics of a low-drag airfoil with a 0.24-chord sealed plain aileron

Description: Report presenting an investigation to determine the effects of forward movements of transition on the section characteristics of a 12-percent-thick low-drag airfoil section with a 0.24-chord sealed plain aileron. Section lift and aileron section hinge-moment and seal-pressure characteristics were determined at a specific Reynolds number for aerodynamically smooth surfaces and with fixed transition at two different points.
Date: May 1948
Creator: Racisz, Stanley F. & Cahill, Jones F.
Item Type: Refine your search to only Report
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