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  • 1
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    Analysis of wind-tunnel stability and control tests in terms of flying qualities of full-scale airplanes (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The analysis of results of wind-tunnel stability and control tests of powered airplane models in terms of the flying qualities of full-scale airplanes is advocated. In order to indicated the topics upon which comments are considered desirable in the report of a wind-tunnel stability and control investigation and to demonstrate the nature of the suggested analysis, the present NACA flying-qualities requirements are discussed in relation to wind-tunnel tests. General procedures for the estimation of flying qualities from wind-tunnel tests are outlined.
    Type: NACA-TR-825
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudder-fixed and rudder-free static directional stability was good. Hinge moment obtained at zero sideslip was satisfactory for determining aileron forces in sideslip.
    Keywords: Aerodynamics
    Type: NACA-WR-L-99 , NACA-ARR-L5H11a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Analysis of wind-tunnel stability and control tests in terms of flying qualities in full-scale airplanes (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-322 , NACA-ARR-3J22
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Stability and control characteristics determined from tests in the Langley 19-foot pressure tunnel of a 0.2375-scale model of the Douglas XA-26 airplane are compared with those measured in flight tests of a Douglas A-26 airplane. Agreement regarding static longitudinal stability as indicated by the elevator-fixed neutral points and by the variation of elevator deflection in both straight and turning flight was found to be good except at speeds approaching the stall. At these low speeds the airplane possessed noticeably improved stability, which was attributed to pronounced stalling at the root of the production wing. The pronounced root stalling did not occur on the smooth, well-faired model wing. Elevator tab effectiveness determined from model tests agreed well with flight-test tab effectiveness, but control-force variations with speed and acceleration were not in good agreement. The use of model hinge-moment data obtained at zero sideslip appeared to be satisfactory for the determination of aileron forces in sideslip. Fairly good correlation in aileron effectiveness and control forces was obtained; fabric distortion may have been responsible to some extent for higher flight values of aileron force at high speeds. Estimation of sideslip developed in an abrupt aileron roll was fair, but determination of the rudder deflection required to maintain zero sideslip in a rapid aileron roll was not entirely satisfactory.
    Type: NACA-TR-816
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A 1/7 scale semispan model of the XB-35 airplane was tested in the Langley 10 foot pressure tunnel, primarily for the purpose of investigating the effectiveness of a leading-edge slot for alleviation of stick-fixed longitudinal instability at high angles of attack caused by early tip stalling and a device for relief of stick-free instability caused by elevon up-floating tendencies at high angles of attack. Results indicated that the slot was not adequate to provide the desired improvement in stick-fixed stability. The tab-flipper device provided improvement in stick-free stability abd two of the linkage combinations tested gave satisfactory variations of control force with airspeed for all conditions except that in which the wing-tip "pitch-control" flap was fully deflected. However, the improvement in control force characteristics was accompanied by a detrimental effect on stick-fixed stability because of the pitching moments produced by the elevon tab deflection.
    Keywords: Aircraft Stability and Control
    Type: NACA-MR-L5L27
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    NASA's High Speed Research Program - An introduction and status report (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: NASA's High Speed Research Program (HSRP) gives attention to the potential environmental effects of a next-generation SST in three areas of concern: atmospheric pollution, airport community noise, and sonic boom. Research has accordingly been undertaken in such fields as the validation of ozone depletion predictions, the feasibility a 90-percent NO(x) emissions reduction to minimize ozone-layer impacts, economically viable compliance with FAR 36 Stage 3 airport community noise levels, and the comparative advantages of efficient subsonic flight over land masses or low-sonic-boom-optimized configurations. Interim HSRP milestones for 1991 and 1992 are noted.
    Keywords: AERONAUTICS (GENERAL)
    Type: SAE PAPER 901923
    Format: text
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    NASA TECHNICAL REPORTS
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