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Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane
Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date:
March 11, 1947
Creator:
Bartlett, Walter A., Jr. & Goral, Edwin B.
System:
The UNT Digital Library
Knock-Limited Performance of Triptane and 28-R Fuel Blends as Affected by Changes in Compression Ratio and in Engine Operating Variables
From Summary: "A knock-limited performance investigation was conducted on blends of triptane and 28-P fuel with a 12-cylinder, V-type, liquid-cooled aircraft engine of 1710-cubic-inch displacement at three compression ratios: 6.65, 7.93, and 9.68. At each compression ratio, the effect of changes in temperature of the inlet air to the auxiliary-stage supercharger and in fuel-air ratio were investigated at engine speeds of 2280 and. 3000 rpm. The results show that knock-limited engine performance, as improved by the use of triptane, allowed operation at both take-off and cruising power at a compression ratio of 9.68."
Date:
March 11, 1947
Creator:
Brun, Rinaldo J.; Feder, Melvin S. & Fisher, William F.
System:
The UNT Digital Library
Full-Scale Investigation of a Wing With the Leading Edge Swept Back 47.5 Degrees and Having Circular-Arc and Finite-Trailing-Edge-Thickness Ailerons
Report presenting an investigation to determine the aerodynamic characteristics of a wing with a leading sweptback edge at 47.5 degrees and a 20-percent-chord, 50-percent-span outboard aileron. The wing had symmetrical circular-arc airfoil sections and was tested with a circular-arc contour aileron and a flat-sided contour aileron with finite trailing-edge thickness. The longitudinal aerodynamic characteristics and aileron effectiveness are provided for both types of ailerons.
Date:
March 11, 1949
Creator:
Lange, Roy H.
System:
The UNT Digital Library
Aerodynamic Measurements Made During Navy Investigation of Human Tolerance to Wind Blasts
From Summary: "This report presents the aerodynamic measurements made during a Navy investigation conducted in the Langley 8-foot high speed tunnel to determine the actual human tolerance to wind blasts."
Date:
March 11, 1947
Creator:
Loving, Donald L.
System:
The UNT Digital Library