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  • 1
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    Trim Drag in the Light of Munk's Stagger Theorem (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Munk's stagger theorem holds that the induced drag of a multiplane is independent of the streamwise position (the stagger) of its lifting elements so long as the gap/span ratios and the element/element lift ratios are specified. In particular, a monoplane-tailplane or a monoplane-foreplane (canard)arrangement can be regarded as a biplane of zero gap and the trim drag due to tailplane download or foreplane upload can be readily calculated. The trim drag penalty is the same for both configurations. Relations are given for trim drag estimates for various practical arrangements.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 319-329
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Propellers of Minimum Induced Loss, and Water Tunnel Tests of Such a Propeller (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The fundamental vortex theory for a single rotation propeller with a finite number of blades is reviewed. The theory leads to the specification of a radial distribution of bound circulation on each blade for minimum induced loss, analogous to the elliptic spanwise distribution of bound circulation on a wing for minimum induced drag. A propeller designed in accord with this theory has been tested in a water tunnel where it exhibited high efficiency in spite of localized cavitating flow. A knowledge of the flow field for an optimum propeller is of value to the airframe designer seeking to maximize the performance of the airplane-propeller combination.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 273-293
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Preservation of wing leading edge suction at the plane of symmetry as a factor in wing-fuselage design (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Most fuselage geometries cover a portion of the wing leading edge near the plane of symmetry, and it seems reasonable to expect that a large fraction of the leading edge suction which would be developed by the covered wing at high angles of attack is not developed on the fuselage. This is one of the reasons that the Oswald span efficiency factor for the wing body combination fails to approach the value predicted by lifting line theory for the isolated wing. Some traditional and recent literature on wing-body interference is discussed and high Reynolds number data on wing-body-nacelle drag are reviewed. An exposed central leading edge geometry has been developed for a sailplane configuration. Low Reynolds number tests have not validated the design concept.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 107-115
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Minimum Vertical Tail Drag (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Tail size requirement calculations are presented for a vertical tail performing a coordinated turn reversal at corresponding load requirements with minimum tail drag.
    Keywords: AERODYNAMICS
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 43-446
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Design of Propellers for Motorsoarers (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A method was developed for the design of propellers of minimum induced loss matched to an arbitrary operating point characterized by disc loading (thrust or power), air density, shaft speed, flight speed, and number of blades. A consistent procedure is outlined to predict the performance of these propellers under off design conditions, or to predict the performance of propellers of general geometry. The examples discussed include a man powered airplane, a hang glider with a 7.5 kW (10 hp) 8,000 rpm engine, and an airplane-like motorsoarer.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center The Sci. and Technol. of Low Speed and Motorless Flight, Pt. 1; p 285-303
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Application of the time vector method to the analysis of flight test lateral oscillation data (1953)
    In:  CASI
    Details
    Publication Date: 2019-05-25
    Keywords: unknown
    Type: CAL-FRM-189
    Format: text
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    NASA TECHNICAL REPORTS
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