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The development and application of high-critical-speed nose inlets

Description: From Summary: "An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum from the standpoint of critical speed has shown that marked similarity exists between the nondimensional profiles of inlets which have widely different proportions and critical speeds. With the nondimensional similarity of such profiles established, the large differences in the critical speeds of these nose inlets must be a function of their proportions. An investigation was underta… more
Date: July 1945
Creator: Baals, Donald D.; Smith, Norman F. & Wright, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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.
Date: November 1945
Creator: Pearson, E. O., Jr.; Evans, A. J. & West, F. E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails

Description: Report presenting an analysis of available data on vee-tail surfaces. The analysis indicated that a vee tail designed to provide values of stability and control parameters equal to those provided by a conventional tail would probably provide no reduction in area unless the conventional vertical tail is in a bad canopy wake or unless the vee tail has a higher effective aspect ratio than the conventional vertical and horizontal tails.
Date: January 1945
Creator: Purser, Paul E. & Campbell, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of the Effect of Horizontal-Tail Flexibility on Longitudinal Control Characteristics

Description: Report presenting an iteration method for determining the longitudinal control characteristics of a flexible horizontal tail. The method permits factors such as the actual spanwise variation of elasticity and the aerodynamic induction effects due to three-dimensional flow to be accounted for to any degree of accuracy needed. An analysis is also included of the effects of horizontal-tail flexibility on the tail effectiveness, the hinge-moment characteristics, and the control-force gradients in a… more
Date: February 1945
Creator: Harmon, S. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: Report presenting an investigation of ailerons with a beveled trialing edge and a blunt-nose overhang of 35 percent aileron chord on an NACA 66(215)-26 airfoil in two-dimensional flow. Five configurations were tested with various modifications of the aileron nose and adjacent airfoil contour to determine the effect of modifications on lift and aileron hinge-moment characteristics.
Date: February 1945
Creator: Bird, J. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Boundary-Layer Transition and Profile Drag of an Experimental Low-Drag Wing Installed on a Fighter-Type Airplane

Description: Report presenting a boundary-layer transition and profile-drag investigation on an experimental low-drag wing installed on a P-47 airplane designated the XP-47F and supplied by the Army Air Forces. Measurements were made at a section outside the propeller slipstream with smooth and with standard camouflage surfaces and on the upper surface of a section in the propeller slipstream with the surface smoothed.
Date: April 1945
Creator: Skoog, Richard B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of Dive-Recovery Flaps on an XP-51 Airplane

Description: Report presenting a flight investigation made to determine the effectiveness of dive-recovery flaps installed on the XP-51 airplane as a safety device for recovery from contemplated terminal-velocity dives. The flap installation is described and results are presented of measurements obtained during stick-free pull-ups and pull-outs made by deflecting the dive-recovery flaps to two selected values of flap angle .
Date: May 1945
Creator: Beeler, De E. & Williams, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a High-Critical-Speed Fuselage Scoop Including the Effects of Boundary Layer

Description: Report presenting a large air scoop designed for high critical speed, which has been tested in the 8-foot high-speed tunnel on the fuselage of a scale fighter-type airplane. The effects of boundary layer on scoop characteristics were found to be important at all inlet-velocity ratios. Results regarding the boundary-layer surveys, characteristics of original scoop installation, and characteristics of scoop with boundary-layer passage are provided.
Date: February 1945
Creator: Smith, Norman F. & Baals, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight investigation of NACA aileron modifications for the improvement of the lateral control characteristics of a high-speed fighter airplane

Description: Report presenting a flight investigation to improve the lateral control of a high-speed fighter airplane. Testing occurred with the original ailerons and a set of modified ailerons, which consisted of an increased balance chord and increased nose radius. The modified ailerons appear to offer a solution to the problem of aileron overbalance and oscillation in high-speed dives.
Date: December 1945
Creator: Williams, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of fixed-stabilizer, adjustable- stabilizer and all-movable horizontal tails

Description: Report presenting an analysis to compare longitudinal stability and control characteristics obtained with a conventional fixed-stabilizer, an adjustable-stabilizer, and an all-movable horizontal tail. The tail-area requirements, control forces required in the critical landing condition, static margin, control-force gradients in a dive recovery, and elevator-free stability are investigated.
Date: October 1945
Creator: Harmon, Sidney M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil

Description: Report presenting an investigation in two-dimensional flow to determine the effect of leakage past the aileron nose on the aerodynamic characteristics of ailerons. The effects of amount and type of leakage, aileron contour, and Mach and Reynolds number are investigated.
Date: July 1945
Creator: Bird, J. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Description: Report presenting an investigation of three interchangeable sealed-gap 0.20-airfoil-chord plain ailerons of different contour on the NACA 65(sub 1)-210 airfoil section. The three aileron contours tested were the true airfoil contour, straight sides, and a beveled trailing edge. Results regarding the aileron effectiveness, aileron hinge moments, lift, pitching moment, and drag are provided.
Date: December 1945
Creator: Underwood, William J.; Braslow, Albert L. & Cahill, Jones F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of the Stability and Control Characteristics of a Tailless All-Wing Airplane Model with Sweepback in the Langley Free-Flight Tunnel

Description: 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. Ele… more
Date: February 1945
Creator: Campbell, John P. & Seacord, Charles L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Wing Modifications on the Longitudinal Stability of a Tailless All-Wing Airplane Model

Description: Report presenting an investigation of the power-off longitudinal stability characteristics of a tailless all-wing airplane model with various wing modifications in the free-flight tunnel. The results indicated that changes in the tip plan form or rotation of the wing tips did not appreciably reduce the instability at high lift coefficients.
Date: September 1945
Creator: Seacord, Charles L., Jr. & Ankenbruck, Herman O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A theoretical analysis of the performance of a diesel engine-compressor-turbine combination for aircraft

Description: Report presenting a theoretical study of a diesel engine-compressor-turbine combination for aircraft application. The performance characteristics of the compressor and turbine chosen for analysis are believed to be attainable on present aircraft equipment.
Date: April 1945
Creator: Hall, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Knock-limited power outputs from a CFR engine using internal coolants 2: six aliphatic amines

Description: Report presenting an investigation to determine the knock-limited performance of AN-F-28, Amendment-2, fuel in a DCFR engine when water solutions of the following aliphatic amines were added as internal coolants: monomethylamine, dimethylamine, ethylendiamine, diethylamine, triethylamine, and butylamine. Results regarding the mean effective pressure, indicated specific fuel competition, indicated specific liquid consumption, and knock-limited inlet-air pressure plotted against fuel-air ratio ar… more
Date: October 1945
Creator: Bellman, Donald R.; Moeckel, W. E. & Evvard, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Electron-Diffraction Examination of Cast-Iron Piston Rings From Single-Cylinder Aircraft Engine Tests

Description: Report presenting an electron-diffraction examination of cast-iron piston rings used in a single-cylinder test engine, which showed the presence of a layer of graphite covering the surface. The wear curves from the rings studied had shown variation from high rates to very low rates of wear.
Date: February 1945
Creator: Nowick, A. S. & Brockway, L. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Electron and X-Ray Diffraction Investigation of Surface Changes on Nitrided-Steel Piston Rings During Engine Operation in Nitrided-Steel Cylinders Barrels

Description: Report presenting an examination of new and used nitrided-steel piston rings by electron and X-ray diffraction in a study of the surface changes produced during engine operation. Both new and used rings, examined after degreasing, gave an electron-diffraction pattern consisting of diffuse bands: those from used rings fell at the usual positions of the bands from polished metal surfaces.
Date: March 1945
Creator: Good, J. N. & Brockway, L. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of the Lift Coefficient on Propeller Flutter

Description: Report presenting flutter of propellers at high angles of attack and flutter data obtained in connection with tests of models of large wind-tunnel propellers. The stall flutter speed was found to be much lower than the calculated classical flutter speed. That flutter speed is only obtainable if the propeller operates at the ideal angle of zero twist.
Date: July 1945
Creator: Theodorsen, Theodore & Regier, Arthur A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Boundary-Layer and Profile-Drag Characteristics of Smooth Wing Sections of a P-47D Airplane

Description: Report presenting a flight investigation made of boundary-layer and profile-drag characteristics of smooth wing sections of a P-47D airplane. Measurements were made at three stations on the wing: boundary-layer measurements, pressure-distribution measurements, and wake surveys. The results indicated that a minimum profile-drag coefficient of 0.0062 for the smooth section at 63 percent semispan was obtained.
Date: October 1945
Creator: Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Boundary-Layer Transition and Profile Drag of an Experimental Low-Drag Wing Installed on a Figher-Type Airplane

Description: Report presenting a boundary-layer-transition and profile-drag investigation conducted on an experimental low-drag wing installed on a P-47 airplane designated the XP-47F. Measurements were made at a section outside the propeller slipstream with smooth and with standard camouflage surfaces and on the upper surface of a section in the propeller slipstream with the surface smoothed. Results regarding the right wing section outside the slipstream and left wing section in the propeller slipstream a… more
Date: April 1945
Creator: Zalovcik, John A. & Skoog, Richard B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Charts for Helicopter-Performance Estimation

Description: Report presenting charts relating helicopter aerodynamic design variables to performance in steady powered flight. The flight conditions covered are hovering, climb, and horizontal flight. The use of the charts is illustrated by numerical examples in order that computations can be made for particular problems.
Date: August 1945
Creator: Talkin, Herbert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Efficiency tests of a single-stage impulse turbine having an 11.0-inch pitch-line diameter wheel with air as the driving fluid

Description: Report presenting efficiency tests on a single-stage impulse turbine with an 11.0-inch pitch-line diameter wheel and a fabricated nozzle diaphragm with air at moderate temperature as the driving fluid. Results regarding the variation of turbine efficiency with blade-to-jet speed ratio over a range of turbine pressure ratios and maximum efficiency are provided.
Date: April 1945
Creator: Gabriel, David S. & Carman, L. Robert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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 tha… more
Date: June 1945
Creator: Gabriel, David S.; Carman, L. Robert & Trautwein, Elmer E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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