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  • 1
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    Comparison of Wind-Tunnel Predictions with Flight Measurements of the Longitudinal-Stability and -Control Characteristics of a Douglas BTD-1 Airplane (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Low Mach number longitudinal-stability and control characteristics as predicted by use of wind tunnel data from a powered 3/16-scale model are compared with flight test measurements of a Navy BTD-1 airplane. The accuracy of the wind tunnel data and the discrepancies involved in attempting to correlate with flight data are discussed and analyzed. The comparison showed that wind tunnel predictions were, in general, in good agreement with flight test data. The predicted values were for the most part sufficiently accurate to show the satisfactory and unsatisfactory characteristics in the preliminary design stage and to indicate possible methods of improvement. The discrepancies which did occur were attributed principally to physical dissimilarities between model and airplane and the instability to determine accurately the flight power conditions. The effect of Mach number was considered negligible since the maximum flight test value was about 0.5. In order to simulate more closely the flight conditions and hence obtain more accurate data for predictions, it appears desirable to perform large-scale tests of unorthodox control surfaces such as the sealed vaned elevators with which the airplane was equipped.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-A6L30
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind-Tunnel Measurements on the Henschel Missile "Zitterrochen" in Subsonic and Supersonic Velocities (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: At the request of the Henschel Aircraft Works. A. G. Berlin. three models of the missile "Zitterrochen" were investigated at subsonic velocities.(open jet 215-millimeter diameter) and at supersonic velocities (open jet 110 by 130 millimeters) in order to determine the effect of various wing forms on the air forces and moments. Three-component measurements were taken, and one model was also investigated with deflected control plates.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1159 , DLUM-3122 , Deutsche Luftfahrtforschung, Untersuchungen und Mitteilungen
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Longitudinal-Stability and -Control Characteristics (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This report contains the flight-test results of the longitudinal-stability and -control phase of a general flying qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). The tests were conducted at indicated airspeeds up to 530 miles per hour (0.76 Mach number) at low altitude and up to 350 miles per hour (0.82) Mach number) at high altitude. These tests showed that the flying qualities of the airplane were in accordance with the requirements of the Army Air Forces Stability and Control Specification except for excessive elevator control forces in maneuvering flight and the inadequacy of the longitudinal trimming control at low airspeeds.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-A7G01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Stick-Fixed Stability and Control Characteristics of the Consolidated Vultee Model 240 Airplane as Estimated from Tests of a 0.092-Scale Powered Model (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Estimates of the static stick-fixed stability and control characteristics of the Consolidated Vultee model 240 airplane are presented in this report. The estimates are based on tests of a 0.092-scale powered model in the 10-foot wind tunnel of the Guggenheim Aeronautical Laboratory of the California Institute of Technology. Results of the analysis are evaluated in terms of the Army specifications for stability and control characteristics which are more specific and, in general, equal to or more rigid than the Civil Aeronautics Administration requirements. The stick-fixed stability and control characteristics of the Consolidated Vultee model 240 were found to be satisfactory except for the following: 1) Marginal longitudinal stability in the landing approach (flaps 30 deg, 50% minimum continuous power) with aft center of gravity (31% M.A.C.); 2) Marginal rudder control to hold zero sideslip in a climb after take-off with asymmetric power (flaps 30 deg, left engine inoperative, right engine delivering take-off power) with maximum rudder throw limited to +/- 18 deg; 3) Marginal dihedral effect with flaps 40 deg and engines delivering maximum continuous power.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-A7F19
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Systematic Wind-Tunnel Measurements on Missiles (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Wind-tunnel measurements on projectiles are discussed. Tests at the Gottingen Tunnel are described. The tunnel operates on the Prandtl principle, that is, a brief stationary air stream produced in an evacuated tank by induction of atmospheric air.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1122 , Lilienthal-Gesellschaft; 139; 29-37
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Theory of Wings in Nonstationary Flow (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: This paper gives an overview of equations for vibration and flutter affecting airplane wings in nonstationary flow.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1154 , Bulletin de L'Academie des Sciences de L'URSS
    Format: application/pdf
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  • 7
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    Preliminary Results of a Free-Flight Investigation of the Static Stability and Aileron Control Characteristics of 1/6 Scale Models of the Bell MX-776 (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of the static longitudinal stability, static directional stability, and aileron control characteristics at transonic and supersonic speeds is being made of 1/6 scale rocket-propelled model of the Bell MX-776. A stability investigation has been made of two symmetrical models with controls undeflected and centers of gravity one-half and one-body diameter, respectively, ahead of the equivalent design center-of-gravity location of the full-scale version. Both models developed large normal-force coefficients in both the subsonic and supersonic ranges which indicated longitudinal instability at low angles of attack. The side-force coefficients were small for both models and indicated that the models were directionally stable. A possible tendency toward dynamic directional instability in the transonic region was indicated by short-period oscillations of the side forces. The results showed a partial-span inboard aileron to be ineffective or to cause negative control in the the transonic region when deflected approximately 5 deg but not when deflected 10 deg. An investigation of drag showed it to increase with a rearward movement of the center of gravity. This indicates an increase in the trim angle of attack as could be caused by a decrease in static stability.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9D21
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Systematic model researches on the stability limits of the DVL series of float designs (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: To determine the trim range in which a seaplane can take off without porpoising, stability tests were made of a Plexiglas model, composed of float, wing, and tailplane, which corresponded to a full-size research airplane. The model and full-size stability limits are in good agreement. After all structural parts pertaining to the air frame were removed gradually, the aerodynamic forces replaced by weight forces, and the moment of inertia and position of the center of gravity changed, no marked change of limits of the stable zone was noticeable. The latter, therefore, is for practical purposes affected only by hydrodynamic phenomena. The stability limits of the DVL family of floats were determined by a systematic investigation independent of any particular sea-plane design, thus a seaplane may be designed to give a run free from porpoising.
    Keywords: Aircraft Stability and Control
    Type: NACA/TM-1254
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 24, 1946 to August 6, 1946 at Orlando, Florida (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The results obtained from gust and draft velocity measurements within thunderstorms for the period July 24, 1946 to August 6, 1946 at Orlando, Florida are presented herein. These data are summarized in tables I and II and are of the type presented in reference 1 for previous flights. In two thunderstorm traverses, indications of ambient-air temperature were obtained from photo-observer records. These data are summarized in table III.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L7C28
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Spin and Recovery Characteristics of the Northrop XF-89 Airplane (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The spin and recovery characteristics of the Northrop XF-89 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape are presented in this report. The characteristics were mainly estimated rather than determined by model tests because the XF-89 dimensional and mass characteristics were such as to make this airplane similar to several others, models of which have previously been tested. Brief tests were made on an available model of similar design to augment the estimation. The results indicate that the recovery characteristics will be satisfactory for all airplane loadings if recovery is attempted by use of rudder followed by moving the elevator down. The rudder pedal forces will be within the capabilities of the pilot but the elevator stick forces will be beyond the pilot's capabilities unless a trim tab, or a booster is used. A 9.5-foot-diameter flat-type tail parachute or a 5.0-foot-diameter flat-type wing-tip parachute with a drag coefficient of 0.7 will be a satisfactory emergency spin-recovery device for spin demonstrations and if it is necessary for the crew to abandon the spinning airplane, they should leave from the outboard side of the cockpit.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9B28a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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