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  • Aircraft Stability and Control  (10)
  • 1955-1959  (7)
  • 1945-1949  (3)
  • 1
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    Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Deg (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight investigation was made at altitudes of 40,000, 25,000 and 15,000 feet to determine the horizontal-tail loads of the Bell X-5 research airplane at a sweep angle of 58.7 deg over the lift range of the airplane for Mach numbers from 0.61 to 1.00. The horizontal-tail loads were found to be nonlinear with lift throughout the lift ranges tested at all Mach numbers except at a Mach number of 1.00. The balancing tail loads reflected the changes which occur in the wing characteristics with increasing angle of attack. The nonlinearities were, in general, more pronounced at the higher angles of attack near the pitch-up where the balancing tail loads indicate that the wing-fuselage combination becomes unstable. No apparent effects of altitude on the balancing tail loads were evident over the comparable lift ranges of these tests at altitudes from 40,000 feet to 15,000 feet. Comparisons of balancing tail loads obtained from flight and windtunnel tests indicated discrepancies in absolute magnitudes, but the general trends of the data agree. Some differences in absolute magnitude may be accounted for by the tail load carried inboard of the strain-gage station and the load induced on the fuselage by the presence of the tail. These loads were not measured in flight.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-H55E20a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Smooth-Water Landing Stability and Rough-Water Landing and Take-Off Behavior of a 1/13-Scale Model of the Consolidated Vultee Skate 7 Seaplane, TED No. NACA DE 338 (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A model of the Consolidated Vultee Aircraft Corporation Skate 7 seaplane was tested in Langley tank no. 2. Presented without discussion in this paper are landing stability in smooth water, maximum normal accelerations occurring during rough-water landings, and take-off behavior in waves.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9H31
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A Flight Investigation of the Low-Speed Handling Qualities of a Tailless Delta-Wing Fighter Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Carrier landing-approach studies of a tailless delta-wing fighter airplane disclosed that approach speeds were limited by ability to control altitude and lateral-directional characteristics. More detailed flight studies of the handling-qualities characteristics of the airplane in the carrier-approach configuration documented a number of factors that contributed to the adverse comments on the lateral-directional characteristics. These were: (1) the tendency of the airplane to roll around the highly inclined longitudinal axis, so that significant sideslip angles developed in the roll as a result only of kinematic effects; (2) reduction of the rolling response to the ailerons because of the large dihedral effect in conjunction with the kinematically developed sideslip angles; and (3) the onset of rudder lock at moderate angles of sideslip at the lowest speeds with wing tanks installed. The first two of the factors listed are inseparably identified with this type of configuration which is being considered for many of the newer designs and may, therefore, represent a problem which will be encountered frequently in the future. The results are of added significance in the demonstration of a typical situation in which extraneous factors occupy so much of the pilot's attention that his capability of coping with the problems of precise flight-path control is reduced, and he accordingly demands a greater speed margin above the stall to allow for airspeed fluctuations.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-15-59A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Static Stability and Control Characteristics of a 0.5-Scale Model of the Hughes GAR-11 Missile at Mach Numbers from 1.60 to 2.30 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Normal forces, axial forces, pitching moments, and rolling moments on the model and hinge moments on each of the four control surfaces were measured. Control surfaces were deflected from -35 deg to 15 deg in various combinations to produce pitching, yawing, and rolling moments on the model over a range of angles of attack from -5 deg to 25 deg at roll angles from -135 deg to 45 deg.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-6-6-59A , AF-AM-162 , A-213 , AF-AM-162
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Tank Tests of a Powered Model of a Compression Plane, NACA Model 171A-2 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The compression plane is intended for operation on or close to the surface of the water, and has a hull with a concave bottom which forms the upper surface of a tunnel into which air is forced under pressure to support part of the load. The results of the tests made in Langley tank no. 1 include values of the horizontal forces, trimming moment, and static pressure in the tunnel for a wide range of loads and speeds and two power conditions, and are presented in the form of curves against speed with load as a parameter. The results are scaled up to 10 times the model size for three conditions at which the model is self-propelled at a steady speed. Lift is obtained from the static pressure of air in the tunnel. In general, the ratio of the gross load to the total resistance increases with increase in load and decrease in speed. This ratio varies between l-7 and 5.7 at high speeds and has a maximum value of 7. The total resistance is nearly the same for both power conditions except at low speeds and heavy loads. No abrupt change in forces on the hull or flow around the hull occurs in. the region of zero draft. The centers of pressure are generally far aft. At the most efficient trim (1.2'), considerable bow-up moment would be required for practicable operation. There is no abrupt transition from the air-borne to the water- borne condition.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8G02
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL55D25 , Rept-4995
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Wind-Tunnel Tests of a 1/8-Scale Powered Model of the XTB3F-1 Airplane, TED No. NACA 2382 (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A 1/8 scale model of the Grumman XTB3F-1 airplane was tested in the Langley 7- by 10-foot tunnel to determine the stability and control characteristics and to provide data for estimating the airplane handling qualities. The report includes longitudinal and lateral stability and control characteristics of the complete model, the characteristics of the isolated horizontal tail, the effects of various flow conditions through the jet duct, tests with external stores attached to the underside of the wing, ana tests simulating landing and take-off conditions with a ground board. The handling characteristics of the airplane have not been computed but some conclusions were indicated by the data. An improvement in the longitudinal stability was obtained by tilting the thrust line down. It is shown that if the wing flap is spring loaded so that the flap deflection varies with airspeed, the airplanes will be less stable than with the flap retracted or fully deflected. An increase in size of the vertical tail and of the dorsal fin gave more desirable yawing-moment characteristics than the original vertical tail and dorsal fin. Preventing air flow through the jet duct system or simulating jet operation with unheated air produced only small changes in the model characteristics. The external stores on the underside of the wing had only small effects on the model characteristics. After completion of the investigation, the model was returned to the contractor for modifications indicated by the test results.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L7G17
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Static Longitudinal and Lateral Stability and Control Data Obtained from Tests of a 1/15-Scale Model of the Goodyear XZP5K Airship, TED No. NACA DE 211 (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Static longitudinal and lateral stability and control data are presented of an investigation on a l/15-scale model of the Goodyear XZP5K airship over a pitch and yaw range of +/-20 deg and 0 deg to 30 deg, respectively, for various rudder and elevator deflections. Two tail configurations of different plan forms were tested and wake and boundary-layer surveys were conducted. Testing was conducted in the Langley full-scale tunnel at a Reynolds number of approximately 16.5 x 10(exp 6) based on hull length, and corresponds to a Mach number of about 0.12.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL56A11
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL55E02 , Rept-5007
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Investigation of the Stability of Very Flat Spins and Analysis of Effects of Applying various Moments Utilizing the Three Moment Equations of Motion (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Based on linearized equations of motion utilizing only the three moment equations and assuming only flat-spin conditions, it appears that contemporary designs (with the moment of inertia about the wing axis I(sub Y) considerably greater than the moment of inertia about the fuselage axis I(sub X) having positive values of C(sub l, sub p) (rolling-moment coefficient due to rolling) or positive values of C(sub l, sub beta) (rolling-moment coefficient due to sideslip) will probably not have a stable spin in the flat-spin region near an angle of attack of 90 deg. If the damping in pitch in flat-spin attitudes is zero, stable flat-spin conditions may not be possible on an airplane having the mass primarily distributed along the wings. The effect of moving ailerons with the spin or the effect of applying a positive pitching moment producing recovery for contemporary fighter designs will be greatest for large negative values of C(sub n, sub beta) (yawing-moment coefficient due to sideslip). In addition, for a certain critical value of positive C(sub n, sub beta), the rolling moment applied by moving ailerons with the spin or the application of a positive pitching moment will have no effect on reducing the spin rate.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-5-25-59L
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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