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  • 1
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    Proportioning the airplane for lateral stability (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Proportioning for lateral aircraft control included: (1) directional stability (slope of curve of yawing moment coefficient against sideslip), and (2) effective dihedral factor (slope of curve of rolling moment coefficient against sideslip). Basic forces influencing the directional stability of aircraft are indicated. Propeller side force, basic fuselage yaw, and vertical tail side force contributed to yaw moment about center of gravity.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 6 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Spin tests of 1/16-scale models of the N3N-3 landplane and seaplane, 12 January 1940 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The test program included the study of both the seaplane and landplane types. On both versions of the model, the effects of loading changes and control dispositions were examined, and on the seaplane, the effect of the cowled and uncowled engine was investigated.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 37 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Spin tests of a 1/20-scale model of the XF4U-1 airplane, 12 July 1939 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: These tests were performed to determine the spinning characteristics of the 1/20-scale model of the XF4U-1 airplane. Effects of loading changes and various control dispositions using both the original and modified vertical tail surfaces were studied. Subsequent tests were made to determine the effects of additional tail modifications.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 47 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Spin tests of a 1/20-scale model of the XP-39 airplane, 15 March 1939 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The tests were performed to determine the spinning characteristics of a 1/20-scale model of the Bell XP-39 airplane. Effects of loading changes and of various control dispositions were studied. Subsequent tests were performed to determine the effect of a change in wing dihedral.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 23 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Lateral stability and control tests of the XP-77 airplane in the NACA full-scale tunnel, 16 June 1944 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Tests were made in the NACA full-scale tunnel to determine the lateral stability and control characteristics of the XP-77 airplane. Measurements were made of the forces and moments on the airplane at various angles of attack and angles of yaw. The measurements were made with the propeller removed and with the propeller installed and operating at various thrust coefficients, and with the landing flaps retracted and deflected. The effects of aileron, elevator, and rudder deflection on control surface effectiveness and hinge moments were determined. The tests were planned to obtain the data required to evaluate as completely as possible the Army Air Force requirements on lateral stability and control for pursuit-type airplanes.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 84 p
    Format: text
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  • 6
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    Spin tests of a low-wing monoplane to investigate scale effect in the model test range, May 1941 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Concurrent tests were performed on a 1/16 and a 1/20 scale model (wing spans of 2.64 and 2.11 ft. respectively) of a modern low wing monoplane in the NACA 15 foot free-spinning wind tunnel. Results are presented in the form of charts that afford a direct comparison between the spins of the two models for a number of different conditions. Qualitatively, the same characteristic effects of control disposition, mass distribution, and dimensional modifications were indicated by both models. Quantitatively, the number of turns for recover and the steady spin parameters, with the exception of the inclination of the wing to the horizontal, were usually in good agreement.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA-TN-807 , Collected Works of Charles J. Donlan; 23 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Characteristics of swept wings at high speeds, 30 January 1952 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Some results of recent swept wing investigations are presented, that were undertaken to determine the effects of thickness and thickness distribution, camber and twist, nose-flap deflection, and devices or fixes for improving the wing pitching moment characteristics at high lift coefficients.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: L52A15 , Collected Works of Charles J. Donlan; 20 p
    Format: text
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  • 8
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    An approximate spin design criterion for monoplanes, 1 May 1939 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, was formulated. The British results were analyzed and applied to American designs. A simpler design criterion, based solely on the type and the dimensions of the tail, was developed; it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NACA-TN-711 , Collected Works of Charles J. Donlan; 11 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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