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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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    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
  • 3
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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
  • 4
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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
  • 5
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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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    NASA TECHNICAL REPORTS
  • 6
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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
  • 7
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    Buffeting of External Fuel Tanks at High Speeds on a Gruman F7F-3 Airplane (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Attempts were made to alleviate the buffeting of external fuel tanks mounted under the wings of a twin-engine Navy fighter airplane. The Mach number at which buffeting began was increased from 0,529 to 0.640 by streamlining the sway braces and by increasing the lateral rigidity of the sway brace system. Further increase of the Mach number, at which buffeting began to 0.725, was obtained by moving the external fuel tank to a position under the fuselage.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SA7A07
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Hydrodynamic Qualities of a 1/10-Size Powered Dynamic Model of the XP5Y-1 Flying Boat in Smooth Water: Langley Tank Model 246, TED No. NACA DE 320 (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The hydrodynamic characteristics of a 1/10-size powered dynamic model of the XP5Y-1 flying boat were determined in Langley tank no. 1. Stable take-offs were possible at all practicable positions of the center of gravity and flap deflections. An increase in gross load from 123.5 to 150.0 pounds (21.5 percent) had only a slight effect on the stable range for take-off. A decrease in forward acceleration from 3.0 to 1.0 feet per second per second had only a very small effect on the stable range for take-off. In general, the landings were free from skipping except at trims below 6 deg where one skip was encountered at an aft position of the center of gravity. The model porpoised during the landing runout at all positions of the center of gravity when landed at trims above 10 deg. Spray in the propellers was light at the design gross load, and was not considered excessive,at a gross load of 136.0 pounds.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9K14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Investigation of the Stability and Control Characteristics of a 1/20-Scale Model of the Consolidated Vultee XB-53 Airplane with a Full-Span Leading-Edge Slat in the Langley Free-Flight Tunnel (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the low-speed; power-off stability and control characteristics of a 1/20-scale model of the Consolidated Vultee XB-53 airplane equipped with full-span leading-edge slats has been conducted in the Langley free-flight tunnel. In this investigation it was found that the-full-span leading-edge slat gave about the same maximum lift coefficient as was obtained with the outboard single slotted flap and inboard slat. The stability and control characteristics were greatly improved except near the stall where the characteristics with the full-span slat were considered unsatisfactory because of a loss of directional stability and a slight nosing-up tendency.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL7L17
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Calibration and Measurement in Turbulence Research by the Hot-Wire Method (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The problem of turbulence in aerodynamics is at present being attacked both theoretically and experimentally. In view of the fact however that purely theoretical considerations have not thus far led to satisfactory results the experimental treatment of the problem is of great importance. Among the different measuring procedures the hot wire methods are so far recognized as the most suitable for investigating the turbulence structure. The several disadvantages of these methods however, in particular those arising from the temperature lag of the wire can greatly impair the measurements and may easily render questionable the entire value of the experiment. The name turbulence is applied to that flow condition in which at any point of the stream the magnitude and direction of the velocity fluctuate arbitrarily about a well definable mean value. This fluctuation imparts a certain whirling characteristic to the flow.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1130 , A Muegyetem Aerodinamikai Intezeteben Keszult Munka
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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