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Results for “Ratio”

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 127 records · Page 7

All sources NASA NTRS DOE OSTI

NASA NTRS1951

Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Plane Tapered Wing of Aspect Ratio 3.1 with 3-percent-thick, Biconvex Section

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Reese, David E↗

NASA NTRS1951

A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2. : Wing-fuselage Configuration Having a Wing of 0 Degrees Sweepback, Aspect Ratio 4.0,taper Ratio 0.6, and NACA 65A006 Ai

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Cahn, Maurice S↗

NASA NTRS1950

A Transonic Wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration Having a Wing of 35 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006

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Henry, Beverly Z , Jr↗

NASA NTRS1951

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution, cambered and twisted for trapezoidal span load distribution

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Phelps, E Ray↗

NASA NTRS1951

Investigation in the Ames 12-foot Pressure Wind Tunnel of a Model Horizontal Tail of Aspect Ratio 3 and Taper Ratio 0.5 Having the Quarter-chord Line Swept Back 45 Degrees

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Kolbe, Carl D↗

NASA NTRS1951

Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degree, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination with a Fuselage at High Subsonic Mach Numbers and Mach Num

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Luoma, Arvo A↗

NASA NTRS1951

Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Plane Triangular Wing of Aspect Ratio 4 with 3-percent-thick, Biconvex Section

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Heitmeyer, John C↗

NASA NTRS1951

The forces and pressure distribution at subsonic speeds on a plane wing having 45 degrees of sweepback, an aspect ratio of 3, and a taper ratio of 0.5

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Kolbe, Carl D↗

NASA NTRS1951

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 3 with NACA 0003-63 section

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Heitmeyer, John C↗

NASA NTRS1951

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 4 with 3-percent-thick rounded nose section

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Heitmeyer, John C↗

NASA NTRS1951

Effects of Spanwise Thickness Variation on the Transonic Aerodynamic Characteristics of Wings Having 35 Degrees of Sweepback, Aspect Ratio 4, and Taper Ratio 0.60

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Morrison, William D , Jr↗

NASA NTRS1951

Small-scale investigation at transonic speeds of the effects of thickening the inboard section of a 45 degrees sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section

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Spreemann, Kenneth P↗

NASA NTRS1952

Aerodynamic Characteristics at Transonic Speeds of a Wing Having a 45 Degree Sweep, Aspect Ratio 8, Taper Ratio 0.45, and Airfoil Sections Varying from the NACA 63A010 Section at the Root to the NACA 63A006 Section at the Tip.

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Morrison, William D , Jr↗

NASA NTRS1952

Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : twisted and cambered triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution

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Heitmeyer, John C↗

NASA NTRS1952

A Transonic Wind-tunnel Investigation of the Aerodynamic Characteristics of Three 4-percent-thick Wings of Sweepback Angles 10.8 Degrees, 35 Degrees, and 47 Degrees, Aspect Ratio 3.5, and Taper Ratio 0.2 in Combination with a Body

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Bielat, Ralph P↗

NASA NTRS1952

Transonic aerodynamic characteristics of three W-plan-form wings having aspect ratio 8, taper ratio 0.45, and NACA-63A-series airfoil sections

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Morrison, William D , Jr↗

NASA NTRS1952

Pressure Distribution at Low Speed on a Model Incorporating a W Wing with Aspect Ratio 6, 45 Degrees Sweep, Taper Ratio 0.6, and an NACA 65A009 Airfoil Section

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Polhamus, Edward C↗

NASA NTRS1952

Preliminary air-flow and thrust calibrations of several conical Cooling-air ejectors with a primary to secondary temperature ratio of 1.0 I : diameter ratios of 1.21 and 1.10

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Greathouse, W K↗