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Results for “Camber”

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 199 records · Page 11

All sources NASA NTRS DOE OSTI

NASA NTRS1949

Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Investigation at a Mach Number of 1.53 to Determine the Effects of Cambering and Twisting the Wing for Uniform Load at a Lift Coefficient of 0.25

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Madden, Robert T↗

NASA NTRS1949

Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Characteristics Throughout the Subsonic Speed Range with the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

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Jones, J Lloyd↗

NASA NTRS1949

A preliminary investigation of the usefulness of camber in obtaining favorable airfoil-section drag characteristics at supercritical speeds

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Nitzberg, Gerald E↗

NASA NTRS1949

Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effects at Subsonic Speeds of a Constant-chord Elevon on a Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

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Jones, J Lloyd↗

NASA NTRS1949

Preliminary Aerodynamic Investigation of the Effect of Camber on a 60 Degree Delta Wing with Round and Beveled Leading Edges

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Riebe, John M↗

NASA NTRS1950

Performance of High-pressure-ratio Axial-flow Compressor Using Highly Cambered NACA 65-series Blower Blades at High Mach Numbers

A complete stage of an axial-flow compressor was designed and built to investigate the possibility of obtaining a high pressure ratio with an acceptable efficiency through the use of the optimum combination of high blade loading and high relative inlet Mach number. Over-all stage performance was investigated over a range of flows at equivalent tip speeds of 418 to 836 feet per second. At design speed (836 ft/sec), a peak total-pressure ration of 1.445 was obtained with an adiabatic efficiency of 0.89. For design angle of attack at the mean radius, a total-pressure ratio of 1.392 was obtained.

COMPRESSORS - AXIAL FLOW↗

NASA NTRS1950

Effects of twist and camber on the low-speed characteristics of a large-scale 45 degree swept-back wing

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Hunton, Lynn W↗

NASA NTRS1950

Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Characteristics at Supersonic Speeds of a Model with the Wing Twisted and Cambered for Uniform Load

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Hall, Charles F↗

NASA NTRS1950

Effect of Compressibility and Camber as Determined from an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-blade Propellers up to Forward Mach Numbers of 0.925

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Carmel, Melvin M↗

NASA NTRS1950

Wind-tunnel Investigation at Low Speed of a Wing Swept-back 63 Degrees and Twisted and Cambered for a Uniform Load at a Lift Coefficient of 0.5

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Weiberg, James A↗

NASA NTRS1950

Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effect of Sideslip on Aerodynamic Characteristics at a Mach Number of 1.4 with the Wing Twisted and Cambered

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Lessing, Henry C↗

NASA NTRS1950

Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effectiveness of an Elevon as a Longitudinal Control and the Effects of Camber and Twist on the Maximum Lift-drag Ratio at Supersonic Speeds

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Olson, Robert N↗

NASA NTRS1950

Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effect of Reynolds Number at Supersonic Mach Numbers on the Longitudinal Characteristics of a Wing Twisted and Cambered for Uniform Load

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Heitmeyer, John C↗

NASA NTRS1950

Wind-tunnel Investigation at Low Speed of a Wing Swept Back 63 Degrees and Twisted and Cambered for Uniform Load at a Lift Coefficient of 0.5 and with a Thickened Tip Section

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Weiberg, James A↗

NASA NTRS1951

The Effects of Increasing the Leading-edge Radius and Adding Forward Camber on the Aerodynamic Characteristics of a Wing with 35 Degrees of Sweepback

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Demele, Fred A↗

NASA NTRS1952

The effect of blade-section camber on the static characteristics of three NACA propellers

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Wood, John H↗

NASA NTRS1951

The Effects of Mach Number and Reynolds Number on the Aerodynamic Characteristics of Several 12-percent-thick Wings Having 35 Degrees of Sweepback and Various Amounts of Camber

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Tinling, Bruce E↗

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↗