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UNT Libraries Government Documents Department
Serial/Series Title:
NACA Aircraft Circulars
Collection:
National Advisory Committee for Aeronautics Collection
- The A.B.C. "Robin" (British) : a single-seat cabin monoplane
- No Description digital.library.unt.edu/ark:/67531/metadc64615/
- The A. B. Flygindustri "K 37" (Swedish Junkers) : A Low-Wing All-Metal Military Airplane
- No Description digital.library.unt.edu/ark:/67531/metadc64629/
- Addition of heat to a compressible fluid in motion
- No Description digital.library.unt.edu/ark:/67531/metadc62512/
- An additional investigation of the high-speed lateral-control characteristics of spoilers
- No Description digital.library.unt.edu/ark:/67531/metadc60955/
- Albatros commercial Airplane L 73
- The Albatros was a two engine commercial biplane carrying 2 pilots, eight passengers, and 160 KG of baggage. The framework is metal, the wings having plywood and fabric over the steel tubing. The L 73 was the first 2 engine biplane to be made in Germany. digital.library.unt.edu/ark:/67531/metadc62075/
- The Albatros L 72A : a German newspaper carrier with slotted wings
- The Albatros 72A is a normal tractor biplane specifically designed to deliver newspapers by dropping them overboard in bundles for ground transport to pick up. It has a 42 ft. wingspan, and a 220 HP B.M.W. engine. digital.library.unt.edu/ark:/67531/metadc61239/
- Albessard "Triavion" Airplane (French) : A Two-Seat Tandem Monoplane
- Autostability is the watchword of this tandem monoplane. The tandem design causes a natural flat flight pattern. It can also land and take off from very short runways. digital.library.unt.edu/ark:/67531/metadc65096/
- All-metal Junkers airplane, type F 13
- No Description digital.library.unt.edu/ark:/67531/metadc57541/
- 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 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/
- 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/
- An analytical investigation of thermal-electric means of preventing ice formations on a propeller blade
- No Description digital.library.unt.edu/ark:/67531/metadc62488/
- Approximate formulas for the computation of turbulent boundary-layer momentum thicknesses in compressible flows
- No Description digital.library.unt.edu/ark:/67531/metadc62569/
- The Avro 627 "Mailplane" (English): A Single-Seat Biplane
- No Description digital.library.unt.edu/ark:/67531/metadc64758/
- The Avro "Avian" Airplane : 65 HP. Armstrong-Siddeley "Genet" engine
- The Avro Avian, designed by Mr. Chadwick of A.V. Roe & Co., Ltd. has a very low structural weight (estimated at 750 lbs. empty) but with sufficient structural integrity to be eligible of an "Aerobatics" certificate from the British Air Ministry. It can be configured as a monoplane, or a biplane with seaplane floats. It is designed for economical production. digital.library.unt.edu/ark:/67531/metadc62129/
- The Avro "Avian III" Airplane (British)
- The Avro Avian has a lift capacity of 828 lbs (including pilot). It is equipped with the Mark II A.D.C. Cirrus engine. digital.library.unt.edu/ark:/67531/metadc65061/
- Avro C.30 Direct-Control Autogiro (British)
- No Description digital.library.unt.edu/ark:/67531/metadc64592/
- Bibliography and review of information relating to the hydrodynamics of seaplanes
- No Description digital.library.unt.edu/ark:/67531/metadc62558/
- The Blackburn "Sprat": A Training Airplane Convertible into Landplane or Seaplane
- The Sprat is similar the Blackburn Swift and Dart models but is designed as a trainer. It is powered with a smaller 275 HP Rolls-Royce Falcon engine. It is a 2 seat biplane with equal sized upper and lower wings. It can quickly convert from a land to a seaplane. digital.library.unt.edu/ark:/67531/metadc61847/
- Blade design data for axial-flow fans and compressors
- No Description digital.library.unt.edu/ark:/67531/metadc62634/
- The Boulton and Paul "Sidestrand I" bomber airplane (British)
- The Sidestrand I is a twin engine bomber that has gone into production for Royal Air Force Squadrons. It seats three, and can carry a load in excess of 3500 lbs. digital.library.unt.edu/ark:/67531/metadc65064/
- The Breguet 270 General-Purpose Military Airplane (French) : A Two-Seat All-Steel Sesquiplane
- No Description digital.library.unt.edu/ark:/67531/metadc64695/
- The Breguet 410 and 411 Military Airplanes (French): Multiplace Sesquiplane Fighters
- No Description digital.library.unt.edu/ark:/67531/metadc64772/
- A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report
- As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required. digital.library.unt.edu/ark:/67531/metadc65165/
- The Bristol "Badminton" Airplane
- The Bristol Badminton, Type 99 airplane has a radial aircooled engine (a Bristol Jupiter 9 cylinder 450 HP.) and three fuel tanks. It is a single seat biplane weighing 1,840 lbs. empty and 2,460 lbs. loaded. digital.library.unt.edu/ark:/67531/metadc62186/
- The Bristol "Bulldog" (British): A Single-Seat All-Steel Fighter
- No Description digital.library.unt.edu/ark:/67531/metadc64623/
- 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/
- Cascade investigation of buckets for a modern aircraft turbosupercharger
- No Description digital.library.unt.edu/ark:/67531/metadc62080/
- Charts for determining propeller efficiency
- No Description digital.library.unt.edu/ark:/67531/metadc62143/
- Charts for estimation of the characteristics of a helicopter rotor in forward flight I : profile drag-lift ratio for untwisted rectangular blades
- No Description digital.library.unt.edu/ark:/67531/metadc61833/
- Charts for helicopter-performance estimation
- No Description digital.library.unt.edu/ark:/67531/metadc61830/
- 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/
- The Cierva "Autogiro" Mark III (British) : Armstrong-Siddeley "Genet Major" Engine
- No Description digital.library.unt.edu/ark:/67531/metadc64674/
- 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/
- Collection of balanced-aileron test data
- No Description digital.library.unt.edu/ark:/67531/metadc61607/
- 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/
- 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/
- Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails
- No Description digital.library.unt.edu/ark:/67531/metadc61649/
- Comparison of Pitching Moments Produced by Plain Flaps and by Spoilers and Some Aerodynamic Characteristics of an NACA 23012 Airfoil with Various Types of Aileron
- Sectional characteristics of airfoil having retractable slotted flap with plain, slot-lip, or retractable ailerons are presented for a large range of aileron deflections. The analysis indicated that pitching moments produced by spoilers were less positive than those produced by plain flaps of equal effectiveness, also that pitching moments created by the spoiler increased less with the Mach number than similar moments produced by plain flaps. Positive values of pitching moment decreased as devices were located nearer airfoil leading edge. digital.library.unt.edu/ark:/67531/metadc61345/
- 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/
- Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived from Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)
- Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects. digital.library.unt.edu/ark:/67531/metadc61347/
- Compressibility Effects in Aeronautical Engineering
- Compressible-flow research, while a relatively new field in aeronautics, is very old, dating back almost to the development of the first firearm. Over the last hundred years, researches have been conducted in the ballistics field, but these results have been of practically no use in aeronautical engineering because the phenomena that have been studied have been the more or less steady supersonic condition of flow. Some work that has been done in connection with steam turbines, particularly nozzle studies, has been of value, In general, however, understanding of compressible-flow phenomena has been very incomplete and permitted no real basis for the solution of aeronautical engineering problems in which.the flow is likely to be unsteady because regions of both subsonic and supersonic speeds may occur. In the early phases of the development of the airplane, speeds were so low that the effects of compressibility could be justifiably ignored. During the last war and immediately after, however, propellers exhibited losses in efficiency as the tip speeds approached the speed of sound, and the first experiments of an aeronautical nature were therefore conducted with propellers. Results of these experiments indicated serious losses of efficiency, but aeronautical engineers were not seriously concerned at the time became it was generally possible. to design propellers with quite low tip. speeds. With the development of new engines having increased power and rotational speeds, however, the problems became of increasing importance. digital.library.unt.edu/ark:/67531/metadc64993/
- Considerations of wake-excited vibratory stress in a pusher propeller
- No Description digital.library.unt.edu/ark:/67531/metadc62151/
- Cooling Characteristics of a Pratt and Whitney R-2800 Engine Installed in an NACA Short-Nose High-Inlet-Velocity Cowling
- An investigation was made of the cooling characteristics of a P and W R-2800 engine with NACA short-nose high inlet-velocity cowling. The internal aerodynamics of the cowling were studied for ranges of propeller-advance ratio and inlet-velocity ratio obtained by deflection of cowling flaps. Tests included variations of engine power, fuel/air ratio and cooling-air pressure drop. Engine cooling data are presented in the form of cooling correlation curves, and an example for calculation of cooling requirements in flight is included. digital.library.unt.edu/ark:/67531/metadc61985/
- 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/
- Correlation of the drag characteristics of a P-51B airplane obtained from high-speed wind-tunnel and flight tests
- No Description digital.library.unt.edu/ark:/67531/metadc60838/
- A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine I
- No Description digital.library.unt.edu/ark:/67531/metadc62295/
- Correlation of Wright Aeronautical Corporation cooling data on the R-3350-14 intermediate engine and comparison with data from the Langley 16-foot high-speed tunnel
- No Description digital.library.unt.edu/ark:/67531/metadc62698/
- Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps
- Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils. digital.library.unt.edu/ark:/67531/metadc61295/