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  • 1
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    Wind-Tunnel Tests of 10-foot-diameter Autogiro Rotors (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of a series of 10-foot-diameter autogiro rotor models tested in the NACA 20-foot wind tunnel. Four of the models differed only in the airfoil sections of the blades, the sections used being the NACA 0012, 0018, 4412, and 4418. Three additional models employing the NACA 0012 section were tested, in which a varying portion of the blade near the hub was replaced by a streamline tube with a chord of about one-fourth the blade chord.
    Type: NACA-TR-552
    Format: application/pdf
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  • 2
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    Wing Pressure Distribution and Rotor-Blade Motion of an Autogiro as Determined in Flight (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests in which the pressure distribution over the fixed wing of an autogiro was determined in both steady and accelerated flight. In the steady-flight condition, the rotor-blade motion was also measured. These data show that in steady flight the rotor speed as a function of the air speed is largely affected by the variation of the division of load between the rotor and the wing; as the load on the wing increases, the rotor speed decreases. In steady flight the presence of the slipstream increased both the wing lift at a given air speed and the maximum lift coefficient of the wing above the corresponding values without the slipstream. In abrupt high-speed turns, the wing attained a normal force coefficient of unity at almost the initial value of the air speed and experienced its maximum load before maximum acceleration occurred.
    Type: NACA-TR-475
    Format: application/pdf
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  • 3
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    The aerodynamic analysis of the gyroplane rotating-wing system (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters. Curves of lift-drag ratio against lift coefficient have been calculated for a typical case, showing the effect of varying the pitch angle, the solidarity, and the average blade-section drag coefficient. The analysis expresses satisfactorily the qualitative relations between the rotor characteristics and the rotor parameters. As disclosed by this investigation, the aerodynamic principles of the gyroplane are sound, and further research on this wing system is justified.
    Type: NACA-TN-492
    Format: application/pdf
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  • 4
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    Simplified aerodynamic analysis of the cyclogiro rotating wing system (1930)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simplified aerodynamic theory of the cyclogiro rotating wing is presented herein. In addition, examples have been calculated showing the effect on the rotor characteristics of varying the design parameters of the rotor. A performance prediction, on the basis of the theory here developed, is appended, showing the performance to be expected of a machine employing this system of sustentation. The aerodynamic principles of the cyclogiro are sound; hovering flight, vertical climb, and a reasonable forward speed may be obtained with a normal expenditure of power. Auto rotation in a gliding descent is available in the event of a power-plant failure.
    Type: NACA-TN-467
    Format: application/pdf
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  • 5
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    Analysis and Model Tests of Autogiro Jump Take-off (1936)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis is made of the autogiro jump take-off, in which the kinetic energy of the rotor turning at excess speed is used to effect a vertical take-off. By the use of suitable approximations, the differential equation of motion of the rotor during this maneuver is reduced to a form that can be solved. Only the vertical jump was studied; the effect of a forward motion during the jump is discussed briefly. The results of model tests of the jump take-off have been incorporated in the paper and used to establish the relative accuracy of the results predicted from the analysis. Good agreement between calculation and experiment was obtained by making justifiable allowances.
    Type: NACA-TN-582
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  • 6
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    A study of autogiro rotor-blade oscillations in the plane of the rotor disk (1936)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis of the factors governing the oscillation of an autogiro rotor blade in the plane of the rotor disk showed that the contribution of the air forces to the resultant motion was small and that the oscillation is essentially a direct effect of the rotor-blade flapping motion. A comparison of calculated oscillations with those measured in flight on three different rotors disclosed that the calculations gave satisfactory agreement with experiment. The calculated air forces on the rotor blade appear to be larger than the experimental ones, but this discrepancy can be attributed to the deficiencies in the strip analysis.
    Type: NACA-TN-581
    Format: application/pdf
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  • 7
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    Wind-tunnel Tests of a Cyclogiro Rotor (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During an extensive study of all types of rotating wings, the NACA examined the cyclogiro rotor and made an aerodynamic analysis of that system (reference 1). The examination disclosed that such a machine had sufficient promise to justify an experimental investigation; a model with a diameter and span of 8 feet was therefore constructed and tested in the 20-foot wind tunnel during 1934. The experimental work included tests of the effect of the motion upon the rotor forces during the static-lift and forward-flight conditions at several rotor speeds and the determination of the relations between the forces generated by the rotor and the power required by it.
    Type: NACA-TN-528
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  • 8
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    Torsion in box wings (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Logical analysis of a box wing necessitates the allowance for the contribution of the drag spars to the torsional strength of the structure. A rigorous analysis is available in the use of the Method of Least Work. The best logical method of analysis is that applying Prandtl's Membrane Analogy. The results so obtained vary by a negligible amount from those obtained by the rigorous method.
    Type: NACA-TN-366
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  • 9
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    An analysis of the factors that determine the periodic twist of an autogiro rotor blade, with a comparison of predicted and measured results (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents an analysis of the factors that determine the periodic twist of a rotor blade under the action of the air forces on it. The results of the analysis show that the Fourier coefficients of the twist are linear expressions involving only the tip-speed ratio, the pitch setting, the inflow coefficient, the pitching-moment coefficient of the blade airfoil section, and the physical characteristics of the rotor blade and machine. The validity of the analysis was examined by using it to predict the twist of a rotor whose twist characteristics had previously been measured in flight. The agreement between the calculated and experimental results was satisfactory.
    Type: NACA-TR-600
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  • 10
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    An analytical and experimental study of the effect of periodic blade twist on the thrust, torque, and flapping motion of an autogiro rotor (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis is made of the influence on autogiro rotor characteristics of a periodic blade twist that varies with the azimuth position of the rotor blade and the results are compared with experimental data. The analysis expresses the influence of this type of twist upon the thrust, torque, and flapping motion of the rotor. The check against experimental data shows that the periodic twist has a pronounced influence on the flapping motion and that this influence is accurately predicted by the analysis. The influence of the twist upon the thrust and torque could be demonstrated only indirectly, but its importance is indicated.
    Type: NACA-TR-591
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