You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Confidential Report
 Collection: National Advisory Committee for Aeronautics Collection
Experiments on drag of revolving disks, cylinders and streamline rods at high speeds
No Description digital.library.unt.edu/ark:/67531/metadc279467/
NACA Mach number indicator for use in high-speed tunnels
No Description digital.library.unt.edu/ark:/67531/metadc279639/
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/
Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight
No Description digital.library.unt.edu/ark:/67531/metadc279640/
On the flow of a compressible fluid by the hodography method II : fundamental set of particular flow solutions of the Chaplygin differential equation
No Description digital.library.unt.edu/ark:/67531/metadc279417/
The propeller and cooling-air-flow characteristics of a twin-engine airplane model equipped with NACA D(sub S)-type cowlings and with propellers of NACA 16-series airfoil sections
No Description digital.library.unt.edu/ark:/67531/metadc279496/
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/
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/
Determination of general relations for the behavior of turbulent boundary layers
No Description digital.library.unt.edu/ark:/67531/metadc279609/
The development and application of high-critical-speed nose inlets
No Description digital.library.unt.edu/ark:/67531/metadc279653/
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/
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine
No Description digital.library.unt.edu/ark:/67531/metadc279622/
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/
An Experimental Investigation of Several Low-Drag Wing-Nacelle Combinations with Internal Air Flow
The results of an experimental investigation of several low-drag wing-nacelle combinations, incorporating internal air-flow systems, are presented. The external-drag increments due to these nacelles are between one-half and two-thirds of those of conventional nacelle forms. This improvement is accomplished with only minor effects on the lift and moment characteristics of the wing. The procedure employed to determine the external shape of such low-drag nacelles is considered in detail. The design of an efficient internal-flow system with or without a blower or throttle, presents no serious problems. The energy losses in the expansion before the engine and the contraction thereafter can be kept small. It is believed that these nacelles have a wide application in housing engine pusher-propeller units and, with some alteration, jet-propulsion devices. It is probable that the low external drags may not be realized if such nacelles are used with a tractor propeller because of the high level of turbulence in the propeller slipstream. digital.library.unt.edu/ark:/67531/metadc64992/
Wind-Tunnel Development of Ailerons for the Curtiss XP-60 Airplanem Special Report
An investigation was made in the LWAL 7- by 10-foot tunnel of internally balanced, sealed ailerons for the Curtiss XP-60 airplane. Ailerons with tabs and. with various amounts of balance were tested. Stick forces were estimated for several aileron arrangements including an arrangement recommended for the airplane. Flight tests of the recommended arrangement are discussed briefly in an appendix, The results of the wind-tunnel and flight tests indicate that the ailerons of large or fast airplanes may be satisfactorily balanced by the method developed. digital.library.unt.edu/ark:/67531/metadc65169/
Correlation of flight data on limit pressure coefficients and their relation to high-speed burbling and critical tail loads
No Description digital.library.unt.edu/ark:/67531/metadc61282/
NACA Radio Ground-Speed System for Aircraft, Special Report
A method that utilizes the Doppler effect on radio signals for determining the speed of an airplane and the distance traveled by the airplane has been developed and found to operate satisfactorily. In this method, called the NACA radio ground-speed system, standard readily available radio equipment is used almost exclusively and extreme frequency stability of the transmitters is not necessary. No complicated equipment need be carried in the airplane, as the standard radio transmitter is usually adequate. Actual flight tests were made in which the method was used and the results were consistent with calibrated air speed indications and stop-watch measurements. Inasmuch as the fundamental accuracy of the radio method is far better than either of the checking systems used, no check was made on the limitations of the accuracy. digital.library.unt.edu/ark:/67531/metadc65161/
Determination of Flight Paths of an SBD-1 Airplane in Simulated Diving Attacks, Special Report
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. digital.library.unt.edu/ark:/67531/metadc65195/
The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies
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. digital.library.unt.edu/ark:/67531/metadc65159/
A method for the rapid estimation of turbulent boundary-layer thickness for calculating profile drag
No Description digital.library.unt.edu/ark:/67531/metadc61265/
The theory of propellers II : method for calculating the axial interference velocity
No Description digital.library.unt.edu/ark:/67531/metadc62138/
Effect of a trailing-edge extension on the characteristics of a propeller section
No Description digital.library.unt.edu/ark:/67531/metadc61477/
The effects of roughness at high Reynolds numbers on the lift and drag characteristics of three thick airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61334/
High-speed investigation of low-drag wing inlets
No Description digital.library.unt.edu/ark:/67531/metadc61335/
Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap
No Description digital.library.unt.edu/ark:/67531/metadc61404/
Simple curves for determining the effects of compressibility on pressure drop through radiators
No Description digital.library.unt.edu/ark:/67531/metadc62021/
Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility
No Description digital.library.unt.edu/ark:/67531/metadc61478/
Charts for determining propeller efficiency
No Description digital.library.unt.edu/ark:/67531/metadc62143/
An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle
No Description digital.library.unt.edu/ark:/67531/metadc62462/
Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel
Force and flight tests were performance on an all-wing model with windmilling propellers. Tests were conducted with deflected and retracted flaps, with and without auxiliary vertical tail surfaces, and with different centers of gravity and trim coefficients. Results indicate serious reduction of stick-fixed longitudinal stability because of wing-tip stalling at high lift coefficient. Directional stability without vertical tail is undesirably low. Low effective dihedral should be maintained. Elevator and rudder control system is satisfactory. digital.library.unt.edu/ark:/67531/metadc60992/
A summary of drag results from recent Langley full scale tunnel tests of Army and Navy airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61174/
Summary of data relating to the effects of wing machine-gun and cannon installations on the aerodynamic characteristics of airplanes
No Description digital.library.unt.edu/ark:/67531/metadc62430/
Effects of compressibility on maximum lift coefficients for six propeller airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61294/
Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails
No Description digital.library.unt.edu/ark:/67531/metadc61494/
The effect of trailing-edge extension flaps on propeller characteristics
No Description digital.library.unt.edu/ark:/67531/metadc62160/
Cascade investigation of buckets for a modern aircraft turbosupercharger
No Description digital.library.unt.edu/ark:/67531/metadc62080/
Climb and high-speed tests of a Curtiss number 714-1C2-12 four-blade propeller on the Republic P-47C airplane
No Description digital.library.unt.edu/ark:/67531/metadc62125/
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/
Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed
No Description digital.library.unt.edu/ark:/67531/metadc61277/
Experimental constriction effects in high-speed wind tunnels
No Description digital.library.unt.edu/ark:/67531/metadc62421/
Physical data on certain alloys for high temperature applications
No Description digital.library.unt.edu/ark:/67531/metadc62224/
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/
Investigations on laminar boundary-layer stability and transition on curved boundaries
No Description digital.library.unt.edu/ark:/67531/metadc62701/
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/
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/
Observations of compressibility phenomena in flight
No Description digital.library.unt.edu/ark:/67531/metadc61129/
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/
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/
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/
FIRST PREV 1 2 3 4 NEXT LAST