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  • Chemical Engineering  (1.166)
  • Cell & Developmental Biology  (654)
  • Aircraft Stability and Control
  • 1960-1964  (1.878)
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  • 1
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    Spin-Tunnel Investigation of a 1/30-Scale Model of the North American A-5 Airplane (1964)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-24
    Beschreibung: An investigation has been made to determine the erect and. inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TM-SX-946 , NACA-AD-3140 , L-3663
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 2
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    Tolerable Limits of Oscillatory Accelerations Due to Rolling Motions Experienced by One Pilot During Automatic-Interceptor Flight Tests (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: Limited flight - test data obtained from an automatically controlled interceptor during runs in which oscillatory rolling motions were encountered have been correlated with the pilot's comments regarding his ability to tolerate the imposed lateral accelerations.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-810 , L-1537
    Format: text
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  • 3
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    Flight Controllability Limits and Related Human Transfer Functions as Determined from Simulator and Flight Tests (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: A simulator study and flight tests were performed to determine the levels of static stability and damping necessary to enable a pilot to control the longitudinal and lateral-directional dynamics of a vehicle for short periods of time. Although a basic set of aerodynamic characteristics was used, the study was conducted so that the results would be applicable to a wide range of flight conditions and configurations. Novel piloting techniques were found which enabled the pilot to control the vehicle at conditions that were otherwise uncontrollable. The influence of several critical factors in altering the controllability limits was also investigated. Several human transfer functions were used which gave fairly good representations of the controllability limits determined experimentally for the short-period longitudinal, directional, and lateral modes. A transfer function with approximately the same gain and phase angle as the pilot at the controlling frequencies along the controllability limits was also derived.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-746 , H-161
    Format: application/pdf
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  • 4
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    The Effect of Lateral- and Longitudinal- Range Control on Allowable Entry Conditions for a Point Return from Space (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The problem of return to a specified landing point on the earth from flight in space is considered by studying the interaction between an assumed control over the lateral and longitudinal range and the initial conditions of approach to the earth, given by orbital-plane inclination, vacuum perigee location, and time of arrival. The maneuvering capability in the atmosphere permits a point return for a range of entry conditions. A lateral-range capability of +/- 500 miles from the center line of an entry trajectory can allow a variation in the time of arrival of over 3.5 hours. Variation in the orbital-plane inclination angle can be as much as +/- 13 deg.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-1067 , A-506
    Format: application/pdf
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  • 5
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    Flutter at Very High Speeds (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: This paper is concerned with a discussion of some of the problems of flutter and aeroelasticity that are or may be important at high speeds. Various theoretical procedures for treating high Mach number flutter are reviewed. Application of two of these methods, namely, the Van Dyke method and piston-theory method, is made to a specific example and compared with linear two- and three-dimensional results. It is shown that the effects of thickness and airfoil shape are destabilizing as compared with linear theory at high Mach number. In order to demonstrate the validity of these large predicted effects, experimental flutter results are shown for two rectangular wings at Mach numbers of 6.86 and 3. The results of nonlinear piston-theory calculations were in good agreement with experiment, whereas the results of using two- and three-dimensional linear theory were not. In addition, some results demonstrating the importance of including camber modes in a flutter analysis are shown, as well as a discussion of one case of flutter due to aerodynamic heating.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-942 , L-1645
    Format: application/pdf
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  • 6
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    Subsonic Kernel-Function Flutter Analysis of a Highly Tapered Tail Surface and Comparison with Experimental Results (1960)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: A flutter analysis employing the kernel function for three-dimensional, subsonic, compressible flow is applied to a flutter-tested tail surface which has an aspect ratio of 3.5, a taper ratio of 0.15, and a leading-edge sweep of 30 deg. Theoretical and experimental results are compared at Mach numbers from 0.75 to 0.98. Good agreement between theoretical and experimental flutter dynamic pressures and frequencies is achieved at Mach numbers to 0.92. At Mach numbers from 0.92 to 0.98, however, a second solution to the flutter determinant results in a spurious theoretical flutter boundary which is at a much lower dynamic pressure and at a much higher frequency than the experimental boundary.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-379 , L-615
    Format: application/pdf
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  • 7
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    Static Longitudinal Stability of a Rocket Vehicle Having a Rear-Facing Step Ahead of the Stabilizing Fins (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: Tests were conducted at Mach numbers of 3.96 and 4.65 in the Langley Unitary Plan wind tunnel to determine the static longitudinal stability characteristics of a fin-stabilized rocket-vehicle configuration which had a rearward facing step located upstream of the fins. Two fin sizes and planforms, a delta and a clipped delta, were tested. The angle of attack was varied from 6 deg to -6 deg and the Reynolds number based on model 6 length was about 10 x 10. The configuration with the larger fins (clipped delta) had a center of pressure slightly rearward of and an initial normal-force-curve slope slightly higher than that of the configuration with the smaller fins (delta) as would be expected. Calculations of the stability parameters gave a slightly lower initial slope of the normal-force curve than measured data, probably because of boundary-layer separation ahead of the step. The calculated center of pressure agreed well with the measured data. Measured and calculated increments in the initial slope of the normal-force curve and in the center of pressure, due to changing fins, were in excellent agreement indicating that separated flow downstream of the step did not influence flow over the fins. This result was consistent with data from schlieren photographs.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-993 , L-1836
    Format: application/pdf
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  • 8
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    Low-Speed Investigation of the Effects of Frequency and Amplitude of Oscillation in Sideslip on the Lateral Stability Derivatives of a 60 deg Delta Wing, a 45 deg Sweptback Wing and an Unswept Wing (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: A low-speed investigation has been conducted in the Langley stability tunnel to study the effects of frequency and amplitude of sideslipping motion on the lateral stability derivatives of a 60 deg. delta wing, a 45 deg. sweptback wing, and an unswept wing. The investigation was made for values of the reduced-frequency parameter of 0.066 and 0.218 and for a range of amplitudes from +/- 2 to +/- 6 deg. The results of the investigation indicated that increasing the frequency of the oscillation generally produced an appreciable change in magnitude of the lateral oscillatory stability derivatives in the higher angle-of-attack range. This effect was greatest for the 60 deg. delta wing and smallest for the unswept wing and generally resulted in a more linear variation of these derivatives with angle of attack. For the relatively high frequency at which the amplitude was varied, there appeared to be little effect on the measured derivatives as a result of the change in amplitude of the oscillation.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-896 , L-1608
    Format: application/pdf
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  • 9
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    Study of an Active Control System for a Spinning Body (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The mission requirements for some satellites require that they spin continuously and at the same time maintain a precise direction of the spin axis. An analog-computer study has been made of an attitude control system which is suitable for such a satellite. The control system provides the necessary attitude control through the use of a spinning wheel, which will provide precession torques, commanded by an automatic closed-loop servomechanism system. The sensors used in the control loop are rate gyroscopes for damping of any wobble motion and a sun seeker for attitude control. The results of the study show that the controller can eliminate the wobble motion of the satellite resulting from a rectangular pulse moment disturbance and then return the spin axis to the reference space axis. The motion is damped to half amplitude in less than one cycle of the wobble motion. The controller can also reduce the motion resulting from a step change in product of inertia both by causing the new principal axis to be steadily alined with the spin vector and by reducing the cone angle generated by the reference body axis. These methods will reduce the motion whether the satellite is a disk, sphere, or rod configuration.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-905 , L-1519
    Format: application/pdf
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  • 10
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    Stability and Control Characteristics of a Model of an Aerial Vehicle Supported by Four Ducted Fans (1961)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The stability and control characteristics of a simple, lightly loaded model approximately one-third the size of a full-scale vehicle have been investigated by a series of free-flight tests. The model is representative of a type of vertically rising aircraft which would utilize four ducted fans as its sole source of lift and propulsion. The ducts were arranged in a rectangular pattern and were fixed to the airframe so that their axes of revolution were vertical for hovering flight. Control moments were provided by remotely controlled compressed-air jets at the sides and ends of the model. In hovering, the model in its original configuration exhibited divergent oscillations about both the roll and pitch axes. Because these oscillations were of a rather short period., the model was very difficult to control by the use of remote controls only. The model could be completely stabilized by the addition of a sufficient amount of artificial damping. The pitching oscillation was made easier to control by increasing the distance between the forward and rearward pairs of ducts. In forward flight, with the model in its original configuration, the top speed was limited by the development of an uncontrollable pitch-up. Large forward tilt angles were required for trim at the highest speeds attained. With the model rotated so that the shorter axis became the longitudinal axis, the pitch trim problem was found to be less than with the longer axis as the longitudinal axis. The installation of a system of vanes in the slipstream of the forward ducts reduced the tilt angle but increased the power required.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NASA-TN-D-937 , L-1482
    Format: application/pdf
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