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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 235 records · Page 13

All sources NASA NTRS DOE OSTI

NASA NTRS1945

Wind-tunnel investigation of control-surface characteristics XXII : medium and large aerodynamic balances of two nose shapes and a plain overhang used with a 0.20-airfoil-chord flap on an NACA 0009 airfoil

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AIRFOILS - NACA 0009 - CHAR , MOMENTS & ORDINATES ↗

NASA NTRS1948

Characteristics of thin triangular wings with constant-chord full-span control surfaces at supersonic speeds

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PITCHING MOMENTS - WINGS, DELTA↗

NASA NTRS1944

Wind-Tunnel Investigation of Control-Surface Characteristics XIX : A Double Flap with an Overhang and an Internal Aerodynamic Balance

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WING FLAPS, DOUBLE↗

NASA NTRS1942

The development of satisfactory flying qualities on the Douglas dive bomber, model SBD-1 through flight testing successive modifications in control-surface area, hinge-line location, and aerodynamic-balance nose shape

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STALLING - DOUGLAS SBD-1↗

NASA NTRS1945

Test of 0.14-Scale Models of the Control Surfaces of Army Project MX-511 in Attitudes Simulating Spins

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CONTROL SURFACES - BELL P-83-WIND TUNNEL TESTS (NA↗

NASA NTRS1968

Optical solar reflector - A highly stable, low alpha sub S/epsilon spacecraft thermal control surface.

Stable optical solar reflector for spacecraft thermal control, summarizing simulated exposures results

Breuch, R. A.↗

NASA NTRS1953

The Influence of the Control-surface-servo Natural Frequency upon the Transient Characteristics of a Flight-path-angle Control System Incorporating a Supersonic Missile

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Passera, Anthony L↗

NASA NTRS1968

Development of phase-change coatings for use as variable thermal control surfaces Final report, 8 Mar. 1967 - 8 Mar. 1968

Development of phase-change coatings for thermal control of spacecraft surfaces

Griffin, R. N.↗

NASA NTRS1948

Characteristics of thin triangular wings with triangular-tip control surfaces at supersonic speeds with Mach lines behind the leading edge

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AIR FLOW VELOCITY, HIGH - SUPERSONIC↗

NASA NTRS1950

Spanwise loading for wings and control surfaces of low aspect ratio

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WINGS - CHARACTERISTICS↗

NASA NTRS1943

Wind-tunnel investigation of control-surface characteristics XIV : NACA 0009 airfoil with a 20-percent-chord double plain flap

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WING FLAPS-OVERHANG↗

NASA NTRS1968

Turbulent heat transfer associated with control surface at Mach 6.

Turbulent heat transfer associated with controls for attached or separated flow analyzed for design of hypersonic cruise aircraft

Emery, J. C.↗

NASA NTRS1942

Notes on the effects of trailing-edge shapes of low-drag airfoils on profile drag and the trim and balance of control surfaces

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AILERONS, CUSP↗

NASA NTRS1941

Wind-tunnel investigation of control-surface characteristics I : effect of gap on the aerodynamic characteristics of an NACA 0009 airfoil with a 30-percent-chord plain flap

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TABS, ELEVATOR↗

NASA NTRS1942

Wind tunnel investigation of control-surface characteristics X : a 30-percent-chord plain flap with straight contour on the NACA 0015 airfoil

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WING FLAPS - EFFECT OF GAPS↗

NASA NTRS1941

Wind-tunnel investigation of control-surface characteristics III : a small aerodynamic balance of various nose shapes used with a 30-percent-chord flap on an NACA 0009 airfoil

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WING FLAPS - DEFLECTION↗

NASA NTRS1975

Prediction of unsteady aerodynamic loadings caused by leading edge and trailing edge control surface motions in subsonic compressible flow: Computer program description

A digital computer program has been developed to calculate unsteady loadings caused by motions of lifting surfaces with leading edge or trailing edge controls based on the subsonic kernel function approach. The pressure singularities at hinge line and side edges have been extracted analytically as a preliminary step to solving the integral equation by collocation. The program calculates generalized aerodynamic forces for user supplied deflection modes. Optional intermediate output includes pressure at an array of points, and sectional generalized forces. From one to six controls on the half span can be accommodated.

Redman, M. C.↗

NASA NTRS1979

Reduction of computer usage costs in predicting unsteady aerodynamic loadings caused by control surface motions: Computer program description

A digital computer program was developed to calculate unsteady loadings caused by motions of lifting surfaces with leading edge and trailing edge controls based on the subsonic kernel function approach. The pressure singularities at hinge line and side edges were extracted analytically as a preliminary step to solving the integral equation of collocation. The program calculates generalized aerodynamic forces for user supplied deflection modes. Optional intermediate output includes pressure at an array of points, and sectional generalized forces. From one to six controls on the half span can be accomodated.

Petrarca, J. R.↗