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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence
No Description digital.library.unt.edu/ark:/67531/metadc53121/
Observations of compressibility phenomena in flight
No Description digital.library.unt.edu/ark:/67531/metadc61129/
Physical data on certain alloys for high temperature applications
No Description digital.library.unt.edu/ark:/67531/metadc62224/
Flight tests of an all-movable vertical tail on the Fairchild XR2K-1 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61509/
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
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. digital.library.unt.edu/ark:/67531/metadc61624/
Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61625/
Determination of general relations for the behavior of turbulent boundary layers
No Description digital.library.unt.edu/ark:/67531/metadc279609/
Flight measurements of compressibility effects on a three-blade thin Clark Y propeller operating at constant advance-diameter ratio and blade angle
No Description digital.library.unt.edu/ark:/67531/metadc62161/
NACA Mach number indicator for use in high-speed tunnels
No Description digital.library.unt.edu/ark:/67531/metadc279639/
Wind-tunnel investigation of control-surface characteristics XIII : various flap overhangs used with a 30-percent-chord flap in an NACA 66-009 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61537/
Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61629/
Calculated and measured turning performance of a Navy F2A-3 airplane as affected by the use of flaps
No Description digital.library.unt.edu/ark:/67531/metadc61133/
Effects of mean-line loading on the aerodynamic characteristics of some low-drag airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61373/
Notes on the effect of surface distortions on the drag and critical Mach number of airfoils
No Description digital.library.unt.edu/ark:/67531/metadc279442/
Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap
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. digital.library.unt.edu/ark:/67531/metadc61398/
Wind-tunnel tests of ailerons at various speeds III : ailerons of 0.20 airfoil chord and true contour with 0.35-aileron-chord Frise balance on the NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61626/
Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section
No Description digital.library.unt.edu/ark:/67531/metadc61406/
Wind tunnel tests of ailerons at various speeds V : pressure distributions over the NACA 66,2-216 and NACA 23012 airfoils with various balances on 0.20-chord ailerons
No Description digital.library.unt.edu/ark:/67531/metadc62593/
A comparison at high speed of the aerodynamic merits of models of medium bombers having thickened wing roots and having wings with nacelles
No Description digital.library.unt.edu/ark:/67531/metadc61167/
Investigation of flow in an axially symmetrical heated jet of air
The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air. (author). digital.library.unt.edu/ark:/67531/metadc65451/
Preliminary aerodynamic and structural tests showing the effect of compressive load on the fairness of a low-drag wing specimen with chordwise hat-section stiffeners
No Description digital.library.unt.edu/ark:/67531/metadc61309/
Wind-tunnel data on the aerodynamic characteristics of airplane control surfaces
No Description digital.library.unt.edu/ark:/67531/metadc61566/
Wind-tunnel investigation of control-surface characteristics XV : various contour modifications of a 0.30-airfoil-chord plain flap on an NACA 66(215)-014 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61545/
Collection of balanced-aileron test data
No Description digital.library.unt.edu/ark:/67531/metadc61607/
Effect of tilt of the propeller axis on the longitudinal-stability characteristics of single-engine airplanes
No Description digital.library.unt.edu/ark:/67531/metadc60951/
The theory of propellers IV : thrust, energy, and efficiency formulas for single- and dual-rotating propellers with ideal circulation distribution
No Description digital.library.unt.edu/ark:/67531/metadc62141/
Wind-tunnel investigation of ailerons on a low-drag airfoil I : the effect of aileron profile
No Description digital.library.unt.edu/ark:/67531/metadc62496/
Wind-tunnel investigation of ailerons on a low-drag airfoil II : the effect of thickened and beveled trailing edges
No Description digital.library.unt.edu/ark:/67531/metadc62493/
Comparison of calculated and experimental propeller characteristics for four-, six-, and eight-blade single-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc62159/
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report
In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included. digital.library.unt.edu/ark:/67531/metadc279600/
Considerations of wake-excited vibratory stress in a pusher propeller
No Description digital.library.unt.edu/ark:/67531/metadc62151/
The determination of span load distribution at high speeds by use of high-speed wind-tunnel section data
No Description digital.library.unt.edu/ark:/67531/metadc61274/
Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers
No Description digital.library.unt.edu/ark:/67531/metadc53376/
Flight investigation of boundary-layer control by suction slots on an NACA 35-215 low-drag airfoil at high Reynolds numbers
No Description digital.library.unt.edu/ark:/67531/metadc61322/
Knock-limited performance of several internal coolants
No Description digital.library.unt.edu/ark:/67531/metadc61936/
Wind-tunnel investigation of control-surface characteristics XVIII : a linked overhang aerodynamic balance
No Description digital.library.unt.edu/ark:/67531/metadc61555/
Experimental study of the coating formed on nitrided-steel piston rings during operation in nitrided-steel cylinders
No Description digital.library.unt.edu/ark:/67531/metadc61990/
High temperature characteristics of 17 alloys at 1200 and 1350 F
No Description digital.library.unt.edu/ark:/67531/metadc62226/
On the flow of a compressible fluid by the hodography method I : unification and extension of present-day results
No Description digital.library.unt.edu/ark:/67531/metadc279666/
Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface
Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results. digital.library.unt.edu/ark:/67531/metadc61579/
Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc62165/
NACA Investigation of a Jet-Propulsion System Applicable to Flight
Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were sufficiently developed to be considered applicable to flight installation. Calculations indicated that an airplane utilizing this jet-propulsion system would have unusual capabilities in the high-speed range above the speeds of conventional aircraft and would, in addition, have moderately long cruising ranges if only the engine were used. digital.library.unt.edu/ark:/67531/metadc279418/
Oxygen boosting of an aircraft-engine cylinder in conjunction with internal coolants
No Description digital.library.unt.edu/ark:/67531/metadc61938/
Preliminary tank tests of an outboard float having the form of a streamline body of revolution fitted with a hydrofoil
No Description digital.library.unt.edu/ark:/67531/metadc61762/
Wind-tunnel investigation of control-surface characteristics XVII : beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61552/
Analysis of available data on control surfaces having plain-overhang and Frise balances
No Description digital.library.unt.edu/ark:/67531/metadc61487/
Analysis of available data on the effectiveness of ailerons without exposed overhang balance
No Description digital.library.unt.edu/ark:/67531/metadc61635/
An analytical investigation of the effects of elevator-fabric distortion on the longitudinal stability and control of an airplane
No Description digital.library.unt.edu/ark:/67531/metadc60987/
Estimation of pressures on cockpit canopies, gun turrets, blisters, and similar protuberances
No Description digital.library.unt.edu/ark:/67531/metadc61703/
Profile-Drag Coefficients of Conventional and Low-Drag Airfoils as Obtained in Flight
Results of flight tests indicate that profile-drag coefficients which were obtained with the low-drag airfoils were lower than with the conventional types over the range of light coefficients tested. For comparable conditions of the lift coefficient and Reynolds Number, the low-drag airfoils have profile-drag coefficients which may be 27 percent lower than the profile drag of the conventional airfoils tested. Detailed results are presented graphically. digital.library.unt.edu/ark:/67531/metadc61320/
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