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  • 11
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    On the Theory of the Unsteady Motion of an Airfoil (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The paper presents a systematical analysis of the problem of the determination of the unsteady motion about an airfoil moving in an infinite fluid that contains a system of vortices and the determination of the hydrodynamical forces acting on the airfoil. The hydrodynamical problem is reduced to the determination of the function f (xi) which transforms conformally the external region of the airfoil into the interior of a circle. The proposed methods of determining the irrotational motion of a fluid that is produced by any motion of the airfoil are especially simple and effective if the function f (xi) is rational. As an example the flow is determined for the case of an arbitrary motion of an airfoil of the Joukowsky type. The formulas obtained for the determination of the hydrodynamical forces by means of contour integration are similar to those given by S. Chaplygin. These formulas are used to determine the force acting on the airfoil in the cases where the unsteady motion is potential throughout and the circulation about the airfoil is constant and also when the fluid contains a system of vortices. A full discussion is given of the concept of virtual masses together with practical formulas for computing the virtual mass coefficients.
    Keywords: Aerodynamics
    Type: NACA-TM-1156
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Measurements in Flight of the Longitudinal-Stability Characteristics of a Republic YF-84A Airplane (Army Serial No. 45-59488) at High Subsonic Mach Numbers (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A brief investigation was made of the longitudinal-stability characteristics of a YF-84A airplane (Army Serial No. 45-79488). The airplane developed a pitching-up tendency at approximately 0.80 Mach number which necessitated large push forces and down-elevator deflections for further increases in speed. In steady turns at 35,000 feet with the center of gravity at 28.3 percent mean aerodynamic chord for normal accelerations up to the maximum test value, the control-force gradients were excessive at Mach numbers over 0.78. Airplane buffeting did not present a serious problem in accelerated or unaccelerated flight at 15,000 and 35,000 feet up to the maximum test Mach number of 0.84. It is believed that excessive control force would be the limiting factor in attaining speeds in excess of 0.84 Mach number, especially at altitudes below 35,000 feet.
    Keywords: Aerodynamics
    Type: NACA-RM-SA8K03
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Tests of an NACA 66,2-420 Airfoil of 5-Foot Chord at High Speed, Special Report (1942)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds including the critical compressibility speed. Section coefficients of lift, drag, and pitching moment, and extensive pressure-distribution data are presented. The section drag coefficient at the design lift coefficient of 0.4 increased from 0.0042 at low speeds to 0.0052 at a Mach number of 0.56 (390 mph at 25,000 ft altitude). The critical Mach number was about 0.60. The results cover a Reynold number range from 4 millions to 17 millions.
    Keywords: Aerodynamics
    Type: NACA-ACR-234 , NACA-SR-234
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    Limitations of Lifting-Line Theory for Estimation of Aileron Hinge-Moment Characteristics (1943)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Hinge-moment parameters for several typical ailerons were calculated from section data with the aspect-ratio correction as usually determined from lifting-line theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory. An additional aspect-ratio correction, calculated by the method of lifting-surface theory, was applied to the slope of the curve of hinge-moment coefficient against angle of attack at small angles of attack. This so-called streamline-curvature correction brought the calculated and experimental results into satisfactory agreement.
    Keywords: Aerodynamics
    Type: AD-A801563 , NACA-WR-L-281 , NACA-CB-3L02
    Format: text
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    NASA TECHNICAL REPORTS
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