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The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds
Report presenting a method for calculating the drag, in a real compressible fluid and at subcritical Mach numbers, of airfoil sections at arbitrary life coefficients and of bodies of revolution at zero angle of attack. The values of drag coefficient are compared with values obtained for the same configurations by other methods. The differences between the results are found to lie withint he limits of accuracy of current experimental techniques.
Date:
April 23, 1947
Creator:
Heaslet, Max A. & Nitzberg, Gerald E.
System:
The UNT Digital Library
Investigation of the aerodynamic and icing characteristics of a recessed fuel cell vent assembly 3: NACA flush-inlet-type vent
An investigation conducted in the icing research tunnel to determine aerodynamic and icing characteristics of two flush-inlet-type fuel cell vent installations. The vent tubes were mounted in two different locations in the two installations. The vents were aerodynamically investigated to obtain vent-tube static-pressure differentials and pressure surveys as a function of tunnel-air velocity and angle of attack.
Date:
April 23, 1948
Creator:
Ruggeri, Robert S.
System:
The UNT Digital Library
Additional Results in a Free-Flight Investigation of Control Effectiveness of Full-Span, 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Aspect Ratio, Taper, and Section Thickness Ratio
Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
Date:
April 23, 1948
Creator:
Sandahl, Carl A. & Strass, H. Kurt
System:
The UNT Digital Library
The Aerodynamic Effects of Rockets and Fuel Tanks Mounted Under the Swept-Back Wing of an Airplane Model
From Summary: "The effects of externally mounted rockets and fuel tanks on the aerodynamic characteristics of an airplane model with a swept-back wing are presented in this report."
Date:
April 23, 1948
Creator:
Boddy, Lee E. & Morrill, Charles P., Jr.
System:
The UNT Digital Library
Empirical mode constants for calculating frequencies of axial-flow compressor blades
The vibration characteristics of a group of axial-flow compressor blades of similar geometry were investigated. Empirical-mode constants were determined for the first three bending and torsional modes. A comparison of experimentally determined frequencies of a second group of blades with frequencies computed using these mode constants showed that the computed values were correct within 10 percent. The approximate limiting ratios of depth to chord and length to chord below which these constants could not be used to compute the natural frequencies were also found experimentally.
Date:
April 23, 1948
Creator:
Millenson, M. B. & Wilterdink, P. I.
System:
The UNT Digital Library
Flight-Test Measurements of Aileron Control Surface Behavior at Super Critical Mach Numbers
Report presenting measurements of the behavior at supercritical Mach numbers of ailerons on a jet-propelled fighter plane. Results regarding aileron upfloat and aileron oscillations are provided.
Date:
April 23, 1947
Creator:
Brown, Harvey H.; Rathert, George A., Jr. & Clousing, Lawrence A.
System:
The UNT Digital Library
Tests of Submerged Duct Installation on the Ryan FR-1 Airplane in the Ames 40- by 80-Foot Wind Tunnel
"An investigation of an NACA submerged intake installation on the Ryan FR-1 was conducted to determine the full-scale aerodynamic characteristics of this installation. In addition, tests were conducted on the submerged inlet with revised entrance lips and deflectors to determine the configuration which would result in the best dynamic pressure recovery measured at the inlet for this installation without a major rework of the entrance. Stalling of the air flow over the inner lip surface created excessive dynamic pressure losses with the original entrance. The revised entrance produced a 12-percent increase in dynamic pressure recovery at the design high-speed inlet-velocity ratio and resulted in an improvement of the critical-speed characteristics of the entrance lip" (p. 1).
Date:
April 23, 1947
Creator:
Martin, Norman J.
System:
The UNT Digital Library