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  • 1
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    Spinning Characteristics of the XN2Y-1 Airplane Obtained from the Spinning Balance and Compared with Results from the Spinning Tunnel and from Flight Tests (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of tests of a 1/10-scale model of the XN2Y-1 airplane tested in the NACA 5-foot vertical wind tunnel in which the six components of forces and moments were measured. The model was tested in 17 attitudes in which the full-scale airplane had been observed to spin, in order to determine the effects of scale, tunnel, and interference. In addition, a series of tests was made to cover the range of angles of attack, angles of sideslip, rates of rotation, and control setting likely to be encountered by a spinning airplane. The data were used to estimate the probable attitudes in steady spins of an airplane in flight and of a model in the free-spinning tunnel. The estimated attitudes of steady spin were compared with attitudes measured in flight and in the spinning tunnel. The results indicate that corrections for certain scale and tunnel effects are necessary to estimate full-scale spinning attitudes from model results.
    Type: NACA-TR-607
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind-tunnel investigation of effect of yawing on lateral-stability characteristics II : rectangular N.A.C.A. 23012 wing with a circular fuselage (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-730
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Spinning Characteristics of Wings V : N.A.C.A. 0009, 23018, and 6718 Monoplane Wings (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Three rectangular monoplane wings having rounded tips were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The airfoil sections used were the N.A.C.A. 0009, 23018, and 6718. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. There is included an estimate of the yawing moment that must be furnished by parts of the airplane to balance the inertia couples and wing yawing moments for spinning equilibrium. The predicted angles of sideslip and yawing moments required for spinning equilibrium for a Clark Y wing with the same form are included for comparison.
    Type: NACA-TN-633
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wind-tunnel Investigation of Effect of Yaw on Lateral-stability Characteristics I : Four N.A.C.A. 23012 Wings of Various Plan Forms with and Without Dihedral (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Four N.A.C.A. 23012 wings were tested at several angles of yaw in the N.A.C.A. 7- by 10-foot wind tunnel. All the wings have rounded tips and, in plan form, one is rectangular and the others are tapered 3:1 with various amounts of sweep. Each wing was tested with two amounts of dihedral and with partial-span split flaps. The coefficients of lift, drag, and pitching moment are given for all the models at zero yaw. The coefficients of rolling moment, yawing moment, and side force are given for the rectangular wing at all values of yaw tested. The rate of change in the coefficients with angle of yaw is given in convenient form for stability calculations.
    Type: NACA-TN-703
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Wind-tunnel tests of several forms of fixed wing slot in combination with a slotted flap on an N.A.C.A. 23012 airfoil (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-702
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Spinning Characteristics of Wings IV : Changes in Stagger of Rectangular Clark Y Cellules (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-625
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effect of stabilizer location upon pitching and yawing moments in spins as shown by tests with the spinning balance (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made with the spinning balance in a 5-foot wind tunnel to study the effect of stabilizer location upon the pitching and yawing moments given by the tail surfaces in spinning attitudes. The tests revealed that the horizontal surfaces, when in a normal location, seriously reduced the effectiveness of the fin and rudder, particularly at angles of attack of 50 degrees or more. The tests also revealed that a more forward or more rearward location gave no consistent or decided improvement; that a lower location greatly increased the shielding so that the yawing moment from the combination was in general less than that given by the bare fuselage; and that a higher location decreased the shielding and gave a favorable interference effect, particularly at the high angles of attack. Additional results regarding the stabilizer and the elevator are given.
    Type: NACA-TN-474
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Spinning characteristics of wings II : rectangular Clark Y biplane cellule: 25 percent stagger; 0 degree decalage; gap/chord 1.0 (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: General methods of theoretical analysis of airplane spinning characteristics have been available for some time. Some of these methods of analysis might be used by designers to predict the spinning characteristics of proposed airplane designs if the necessary aerodynamic data were known. The present investigation, to determine the spinning characteristics of wings, is planned to include variations in airfoil sections, plan forms, and tip shapes of monoplane wings and variations in stagger, gap, and decalage for biplane cellules. The first series of tests, made on a rectangular Clark Y monoplane wing, are reported in reference 1. That report also gives an analysis of the data for predicting the probable effects of various important parameters on the spin for normal airplanes using such a wing. The present report is the second of the series. It gives the aerodynamic characteristics of a rectangular Clark Y biplane cellule in spinning attitudes and includes a discussion of the data, using the method of analysis given in reference 1.
    Type: NACA-TN-526
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    The Aerodynamic Forces and Moments on a Spinning Model of the F4B-2 Airplane as Measured by the Spinning Balance (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerodynamic forces and moments on a 1/12-scale model of the F4B-2 airplane were measured with the spinning balance in nine spinning attitudes with three sets of tail surfaces, namely, F4B-2 surfaces; F4B-4 fin and rudder with rectangular stabilizer; and with all tail surfaces removed. In one of these attitudes measurements were made to determine the effect upon the forces and moments of independent and of simultaneous displacement of the rudder and elevator for two of the sets of tail surfaces. Additional measurements were made for a comparison of model and full-scale data for six attitudes that were determined from flight tests with various control settings. The characteristics were found to vary in the usual manner with angle of attack and sideslip. The F4B-2 surfaces were quite ineffective as a source of yawing moments. The F4B-4 fin and F4B-2 stabilizer gave a greater damping yawing moment when controls were against the spin than did the F4B-2 surfaces but otherwise there was little difference. Substitution of a rectangular stabilizer for the F4B-2 stabilizer made no appreciable difference in the coefficient. Further comparisons with other airplane types are necessary before final conclusions can be drawn as to the relations between model and full-scale spin measurements.
    Type: NACA-TN-517
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Aerodynamic effects of a split flap on the spinning characteristics of a monoplane model (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The investigation described in this report was made to determine the change in aerodynamic forces and moments produced by split flaps in a steady spin. The test were made with the spinning balance in the NACA 5-foot vertical wind tunnel. A low-wing monoplane model was tested with and without the split flaps in 12 spinning attitudes chosen to cover the probable spinning range. The changes in coefficients produced by adding the split flaps are given for longitudinal force, normal force, and rolling and yawing moments about body axes. The results obtained indicate that the use of split flaps on an airplane is unlikely, in any case, to have much beneficial effect on a spin, and it might make the spin dangerous. The change in the spin will depend upon the aerodynamic and inertia characteristics of the particular airplane. A dangerous condition is most likely to be attained with airplanes which are statically stable in yaw in the spinning attitude and which have large weights distributed along wings.
    Type: NACA-TN-515
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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