You limited your search to:
Year:
1945
Serial/Series Title:
NACA Advanced Confidential Report
Serial/Series Title:
NACA Aircraft Circulars
Serial/Series Title:
NACA Wartime Reports
Collection:
Technical Report Archive and Image Library
- Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade
- As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions. digital.library.unt.edu/ark:/67531/metadc63062/
- 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 metallurgical investigation of a large forged disc of 19-9 DL alloy
- No Description digital.library.unt.edu/ark:/67531/metadc62273/
- The effect of trailing-edge extension flaps on propeller characteristics
- No Description digital.library.unt.edu/ark:/67531/metadc62160/
- 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/
- Supersonic-tunnel tests of projectiles in Germany and Italy
- No Description digital.library.unt.edu/ark:/67531/metadc62434/
- Effect of the lift coefficient on propeller flutter
- No Description digital.library.unt.edu/ark:/67531/metadc62153/
- Knock-limited power outputs from a CFR engine using internal coolants II : six aliphatic amines
- No Description digital.library.unt.edu/ark:/67531/metadc62055/
- Blade design data for axial-flow fans and compressors
- No Description digital.library.unt.edu/ark:/67531/metadc62634/
- Preliminary Investigation of Supersonic Diffusers
- No Description digital.library.unt.edu/ark:/67531/metadc62636/
- 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/
- An infrared cloud indicator I : analysis of infrared-radiation exchange with tables and chart for calibration of the cloud indicator
- No Description digital.library.unt.edu/ark:/67531/metadc62395/
- A theoretical analysis of the performance of a diesel engine-compressor-turbine combination for aircraft
- No Description digital.library.unt.edu/ark:/67531/metadc62106/
- Addition of heat to a compressible fluid in motion
- No Description digital.library.unt.edu/ark:/67531/metadc62512/
- Rubber conductors for aircraft ignition cables
- No Description digital.library.unt.edu/ark:/67531/metadc62514/
- Bibliography and review of information relating to the hydrodynamics of seaplanes
- No Description digital.library.unt.edu/ark:/67531/metadc62558/
- An electron and x-ray diffraction investigation of surface changes on nitrided-steel piston rings during engine operation in nitrided-steel cylinders barrels
- No Description digital.library.unt.edu/ark:/67531/metadc62002/
- Investigation of boundary layer transition on concave walls
- No Description digital.library.unt.edu/ark:/67531/metadc62676/
- 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/
- Performance of compressor-turbine jet-propulsion systems
- No Description digital.library.unt.edu/ark:/67531/metadc62464/
- Summary of Airfoil Data
- Recent airfoil data for both flight and wind-tunnel tests have been collected and correlated insofar as possible. The flight data consist largely of drag measurements made by the wake-survey method. Most of the data on airfoil section characteristics were obtained in the Langley two-dimensional low-turbulence pressure tunnel. Detail data necessary for the application of NACA 6-serles airfoils to wing design are presented in supplementary figures, together with recent data for the NACA 24-, 44-, and 230-series airfoils. The general methods used to derive the basic thickness forms for NACA 6- and 7-series airfoils and their corresponding pressure distributions are presented. Data and methods are given for rapidly obtaining the approximate pressure distributions for NACA four-digit, five-digit, 6-, and 7-series airfoils. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed. The data indicate that the effects of surface condition on the lift and drag characteristics are at least as large as the effects of the airfoil shape and must be considered in airfoil selection and the prediction of wing characteristics. Airfoils permitting extensive laminar flow, such as the NACA 6-series airfoils, have much lower drag coefficients at high speed and cruising lift coefficients than earlier types-of airfoils if, and only if, the wing surfaces are sufficiently smooth and fair. The NACA 6-series airfoils also have favorable critical-speed characteristics and do not appear to present unusual problems associated with the application of high-lift and lateral-control devices. Much of the data given in the NACA Advance Confidential Report entitled "Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Number and Low Turbulence," by Eastman N. Jacobs, Ira R. Abbott, and Milton Davidson, March 1942 has been corrected and included in the present paper, which supersedes the previously published paper. digital.library.unt.edu/ark:/67531/metadc61319/
- Effects on low-speed spray characteristics of various modifications to a powered model of the Boeing XPBB-1 flying boat
- No Description digital.library.unt.edu/ark:/67531/metadc61764/
- Flight investigation of boundary-layer transition and profile drag of an experimental low-drag wing installed on a fighter-type airplane
- No Description digital.library.unt.edu/ark:/67531/metadc61735/
- Flight tests of dive-recovery flaps on an XP-51 airplane
- No Description digital.library.unt.edu/ark:/67531/metadc61739/
- Effect of wing modifications on the longitudinal stability of a tailless all-wing airplane model
- No Description digital.library.unt.edu/ark:/67531/metadc61001/
- A simple method for estimating terminal velocity including effect of compressibility on drag
- No Description digital.library.unt.edu/ark:/67531/metadc61252/
- An electron-diffraction examination of cast-iron piston rings from single-cylinder aircraft engine tests
- No Description digital.library.unt.edu/ark:/67531/metadc61999/
- Efficiency tests of a single-stage impulse turbine having an 11.0-inch pitch-line diameter wheel with air as the driving fluid
- No Description digital.library.unt.edu/ark:/67531/metadc61858/
- The Effect of Inlet Pressure and Temperature on the Efficiency of a Single Stage Impulse Turbine Having an 11.0-Inch Pitch-Line Diameter Wheel
- Efficiency tests have been conducted on a single-stage impulse engine having an 11-inch pitch-line diameter wheel with inserted buckets and a fabricated nozzle diaphragm. The tests were made to determine the effect of inlet pressure, Inlet temperature, speed, and pressure ratio on the turbine efficiency. An analysis is presented that relates the effect of inlet pressure and temperature to the Reynolds number of the flow. The agreement between the analysis and the experimental data indicates that the changes in turbine efficiency with Inlet pressure and temperature may be principally a Reynolds number effect. digital.library.unt.edu/ark:/67531/metadc61859/
- 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/
- Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modifications of aileron nose and adjacent airfoil contour
- No Description digital.library.unt.edu/ark:/67531/metadc61632/
- Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil
- No Description digital.library.unt.edu/ark:/67531/metadc61639/
- Effects of compressibility on maximum lift coefficients for six propeller airfoils
- No Description digital.library.unt.edu/ark:/67531/metadc61294/
- Wind-tunnel investigation of a high-critical-speed fuselage scoop including the effects of boundary layer
- No Description digital.library.unt.edu/ark:/67531/metadc61665/
- A flight investigation of NACA aileron modifications for the improvement of the lateral control characteristics of a high-speed fighter airplane
- No Description digital.library.unt.edu/ark:/67531/metadc61647/
- 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/
- Determination of the effect of horizontal-tail flexibility on longitudinal control characteristics
- No Description digital.library.unt.edu/ark:/67531/metadc61496/
- Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes
- No Description digital.library.unt.edu/ark:/67531/metadc61175/
- Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section
- No Description digital.library.unt.edu/ark:/67531/metadc61394/
- Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails
- No Description digital.library.unt.edu/ark:/67531/metadc61649/
- Charts for helicopter-performance estimation
- No Description digital.library.unt.edu/ark:/67531/metadc61830/
- 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/
- Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing
- No Description digital.library.unt.edu/ark:/67531/metadc61342/
- 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/
- Flight investigation of the variation of drag coefficient with Mach number for the Bell P-39N-1 airplane
- No Description digital.library.unt.edu/ark:/67531/metadc61128/
- Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-Foot-Span Fighter-Type Wing of NACA 230-Series Airfoil Sections
- Lift characteristics and pressure distribution for a NACA 230 wing were investigated for an angle of attack range of from -10 to +24 degrees and Mach range of from 0.2 to 0.7. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward. digital.library.unt.edu/ark:/67531/metadc61423/
- 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/
- An additional investigation of the high-speed lateral-control characteristics of spoilers
- No Description digital.library.unt.edu/ark:/67531/metadc60955/