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  • Aerodynamics  (13)
  • Aircraft Stability and Control  (3)
  • 1940-1944  (16)
  • 1943  (16)
  • 1
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    Antispin-Tail-Parachute Installations (1943)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-05
    Beschreibung: Although antispin tail parachutes have been used successfully in spin demonstrations for some time, very little published information is available concerning the size of parachute, the bridle-line length, and the type and location of pack to use for particular airplane. The present paper is an attempt to supply data relating to these factors. The paper is in two parts. The first part reviews the principles of operation of the antispin parachutes, views the principles of operation of the antispin parachutes, summarized available information on actual installations, and discusses parachute loads and pack locations. The second part of the paper reports on systematic tests in the NACA-15-foot and 20-foot free-spinning tunnels at the Langley memorial Aeronautical Laboratory to determine the minimum size and the optimum bridle-line lengths for antispin tail parachutes for current military airplanes. It is concluded that airplanes weighing between 7500 and 14,000 pounds require parachutes 8 feet in diameter and bridle-line lengths between 20 and 50 feet. A positive-ejection mechanism is desirable to throw the parachute clear of the tail and to assure rapid opening. The pack and attachment point must be so located that the equipment will not foul the tail surfaces.
    Schlagwort(e): Aircraft Stability and Control
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-416
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    Wind-Tunnel Investigation of a Revised Horizontal Tail Surface for the Grumman TBF-1 Airplane (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-702
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
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    Drag Measurements of a Protruding .50-caliber Machine Gun with Barrel Jacket Removed (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Tests were made in 8-ft high-speed wind tunnel to determine the drag reduction possible by eliminating the barrel jacket of a protruding 50-caliber aircraft gun. It was found that the drag of a standard aircraft gun protruding into the air stream at right angles to the flow can be reduced by 23% by discarding the barrel jacket. At 300 mph and sea-level conditions, this amounts to a decrease in drag of from 83 to 64 pounds. A rough surface finish on the barrel was found to have no adverse effects on the drag of the barrel, the drag being actually less at high Mach Numbers.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-581
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
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    Flight Tests of Various Tail Modifications on the Brewster XSBA-1 Airplane II : Measurements of Flying Qualities with Tail Configuration Number Two (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Several tail modifications of the Brewster XSBA-1 scout-bomber were investigated and results compared. Modifications consisted of variation of the chord of the elevator and rudder while the total area of the surfaces is kept constant and variations of the total area of the vertical tail surface. Configuration number 2 reduced trim changes by 50 percent and reduced average elevator control force gradient from 30 to 27 pounds/g. Stick travel required to stall in maneuver was 4.6 inches.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-598
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
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    Wind-Tunnel Tests of the 1/9-Scale Model of the Curtiss XP-62 Airplane with Various Vertical Tail Arrangements (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The effect of various vertical tail arrangements upon the stability and control characteristics of an XP-62 fighter model was investigated. Rudder-free yaw characteristics with take-off power and flaps deflected were satisfactory after dorsal fin modifications. Directional stability was obtained with all modified vertical tails. Satisfactory rudder effectiveness resulted partly because the dual-rotation propellers produced no asymmetric yawing moments. Pedal forces in sideslips were undesirably large but may be easily reduced.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-WR-L-779
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 7
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    Wind Tunnel Tests of Ailerons at Various Speeds I : Ailerons of 0.20 Airfoil Chord and True Contour with 0.35 Aileron-chord Extreme Blunt Nose Balance on the NACA 66,2-216 Airfoil (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-431 , NACA-ACR-3F11
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
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    Wind-Tunnel Investigation of a Plain Aileron with Various Trailing-Edge Modifications on a Tapered Wing III : Ailerons with Simple and Spring-Linked Balancing Tabs (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Aerodynamics data are obtained for the design of linked balancing tabs and effect of varied tab span and location to produce suitable lateral control characteristics with reasonable stick pressures for high-speed aircraft. Simple and spring-linked balancing tabs may considerably reduce control pressures if aileron system is designed for low maximum aileron deflection. Spring-linked tabs also decrease variation of stick pressure with speed and impart better controlllability at low speeds.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-470
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 9
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    Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-697 , NACA-ACR-3I20
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 10
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    Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-262
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 11
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    The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-WR-L-388 , NACA-ARR-3H31
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 12
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    Methods of Measurement of High Air Velocities by the Hot-wire Method (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Investigations of strengths of hot wires at high velocities were conducted with platinum, nickel, and tungsten at approximately 200 Degrees Celcius hot-wire temperature. The results appear to disqualify platinum for velocities approaching the sonic range; whereas nickel withstands sound velocity, and tungsten may be used for supersonic velocities under standard atmospheric conditions. Hot wires must be supported by rigid prolongs at high velocities to avoid wire breakage. Resting current measurements for constant temperature show agreement with King's relation.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-880
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 13
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    Preliminary Investigation of the Effect of Compressibility on the Maximum Lift Coefficient, Special Report (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-ACR-246 , NACA-SR-246
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 14
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    Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation has been made to determine the motions of and the flight paths describe by a Navy dive-bombing airplane in simulated diving attacks. The data necessary to evaluate these items, with the exception of the atmospheric wind data, were obtained from automatic recording instruments installed entirely within the airplane. The atmospheric wind data were obtained from the ground by the balloon-theodolite method. The results of typical dives at various dive angles are presented in the form of time histories of the motion of the airplane as well as flight paths calculated with respect to still air and with respect to the ground.
    Schlagwort(e): Aircraft Stability and Control
    Materialart: NACA-ACR-248 , NACA-SR-248
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 15
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    The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies (1943)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It i s shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients . The available data indicate that for low-drag and high critical compressibility speed airfoils and bodies of revolution, this effect is favorable.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-ACR-252 , NACA-SR-252
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 16
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    Limitations of Lifting-Line Theory for Estimation of Aileron Hinge-Moment Characteristics (1943)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Hinge-moment parameters for several typical ailerons were calculated from section data with the aspect-ratio correction as usually determined from lifting-line theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory. An additional aspect-ratio correction, calculated by the method of lifting-surface theory, was applied to the slope of the curve of hinge-moment coefficient against angle of attack at small angles of attack. This so-called streamline-curvature correction brought the calculated and experimental results into satisfactory agreement.
    Schlagwort(e): Aerodynamics
    Materialart: AD-A801563 , NACA-WR-L-281 , NACA-CB-3L02
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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