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Two-dimensional wind-tunnel investigation at high Reynolds numbers of two symmetrical circular-arc airfoil sections with high-lift devices

Description: Report presenting an investigation of two symmetrical circular-arc airfoils of 6 and 10 percent thickness equipped with leading-edge and trailing-edge high-lift devices. A trialing-edge flap, drooped-nose flap, and leading-edge extensible flap were all tested. Results regarding the plain airfoils, airfoils with high-lift devices, combined deflection of high-lift devices, and low-drag-control flaps are provided.
Date: March 12, 1947
Creator: Underwood, William J. & Nuber, Robert J.
Item Type: Refine your search to only Report
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Knock-Limited Performance of Triptane and 28-R Fuel Blends as Affected by Changes in Compression Ratio and in Engine Operating Variables

Description: From Summary: "A knock-limited performance investigation was conducted on blends of triptane and 28-P fuel with a 12-cylinder, V-type, liquid-cooled aircraft engine of 1710-cubic-inch displacement at three compression ratios: 6.65, 7.93, and 9.68. At each compression ratio, the effect of changes in temperature of the inlet air to the auxiliary-stage supercharger and in fuel-air ratio were investigated at engine speeds of 2280 and. 3000 rpm. The results show that knock-limited engine performance… more
Date: March 11, 1947
Creator: Brun, Rinaldo J.; Feder, Melvin S. & Fisher, William F.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

Description: Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date: March 11, 1947
Creator: Bartlett, Walter A., Jr. & Goral, Edwin B.
Item Type: Refine your search to only Report
open access

Ditching Tests of a 1/18-Scale Model of the Navy XP4M-1 Airplane in Langley Tank No. 2 and on an Outdoor Catapult, TED No. NACA 2362

Description: From Summary: "Tests with a dynamically similar model of the Navy XP4M-1 airplane were made to determine the best way to land the airplane in calm and rough water, to determine its probable ditching performance, and to determine practicable modifications which could be incorporated in the design of the airplane that would improve its ditching characteristics. The results were obtained by making visual observations, by recording longitudinal decelerations ,and by taking motion pictures of the la… more
Date: March 10, 1947
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
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Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 22, 1946 to July 23, 1946 at Orlando, Florida

Description: "The results obtained from measurements of gust and draft velocities within thunderstorms for the period July 22, 1946 to July 23, 1946 at Orlando, Florida, are presented herein. These data are summarized in tables I and II, respectively, and are of the type presented in reference 1 for previous flights. Inspection of photo-observer records for the flights indicated that no data on ambient air temperature variations within thunderstorms were obtained" (p. 1).
Date: March 10, 1947
Creator: Tolefson, H. B.
Item Type: Refine your search to only Report
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Drag Measurements of Symmetrical Circular-Arc and NACA 65-009 Rectangular Airfoils Having an Aspect Ratio of 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report discussing testing to determine the drag characteristics at zero lift of a wing with a circular-arc airfoil section with a maximum thickness of 9 percent chord. The results were compared to previous testing on an NACA 65-009 airfoil. It was found that the NACA airfoil had lower drag coefficients than the circular-arc airfoil tested in this experiment.
Date: March 7, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
open access

Comparative Drag Measurements at Transonic Speeds of an NACA 65-006 Airfoil and a Symmetrical Circular-Arc Airfoil

Description: Report presenting measurements made at transonic speeds by the freely-falling-body method to compare the drag of a rectangular plan-form airfoil of aspect ratio 7.6 with an NACA 65-006 airfoil section. Results regarding the velocity measurements, base-pressure measurements, and airfoil drag measurements are provided.
Date: March 6, 1947
Creator: Thompson, Jim Rogers & Marschner, Bernard W.
Item Type: Refine your search to only Report
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Ditching Tests with a 1/12-Scale Model of the Army A-26 Airplane in Langley Tank No. 2 and on an Outdoor Catapult

Description: Tests were conducted in calm water in Langley tank no. 2 and in calm and rough water at an outdoor catapult in order to determine the best way to make a forced landing of an Army A-26 airplane and to determine its probable ditching behavior. These tests were requested by the Air Materiel Command, Army Air Forces, in their letter of March 26, 1943, WEL:AW:50.
Date: March 6, 1947
Creator: Jarvis, George A. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

Free-Spinning and Tumbling Tests of a 1/16-Scale Model of the McDonnell XP-85 Airplane

Description: The teat results showed that with either of the three tail arrangements, the model usually spun in flat attitudes with oscillations about the lateral and longitudinal axes. In general, full reversal of the rudder pedals did not stop the spinning rotation. To make the model satisfactorily meet-the spin-recovery requirements it was found that installation of either a very large ventral fin (l7.9 square feet, full scale) below the tail or a somewhat smaller ventral fin and rudder (12.4 square feet… more
Date: March 6, 1947
Creator: Klinar, Walter J.
Item Type: Refine your search to only Report
open access

Investigation of the Trim Characteristics of a 1/20-Scale Model of the Fleetwings XBTK-1 Airplane over a Wide Range of Angles of Attack

Description: "Tests of a 1/20-scale model of the Fleetwings XBTK-1 airplane have been performed in the Langley 15-foot free-spinning tunnel to determine the trim tendencies of the airplane at attitudes above the stall. The results of the tests indicated that the model would trim longitudinally only in the normal range of angles of attack and that the yaw trim tendencies for such longitudinal trim conditions were normal. Although wide oscillations in yaw were noted for some conditions, they occurred at angle… more
Date: March 5, 1947
Creator: Stone, Ralph W., Jr. & Berman, Theodore
Item Type: Refine your search to only Report
open access

Summary of Available Data Relating to Reynolds Number Effects on the Maximum Lift Coefficients of Swept-Back Wings

Description: The available foreign and American data relating to Reynolds number effects on the maximum lift coefficients of swept-back wings are summarized and discussed. The data show that at low Reynolds numbers (below about 2.0 x 10(exp 6)) higher maximum lift coefficients were measured in most cases for moderately swept-back wings than for unswept wings of similar plan form; at high Reynolds numbers, however, increasing sweepback resulted in decreasing maximum lift coefficients. A smaller rate of incre… more
Date: March 4, 1947
Creator: Sweberg, Harold H. & Lange, Roy H.
Item Type: Refine your search to only Report
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Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys

Description: "A method is described by which the total temperature of the gases at the combustion-chamber outlet of a ram-jet engine may be determined from the loss in total pressure measured across the combustion chamber. A working chart is presented by means of which the ratio of the total temperature of the gases at the combustion-chamber outlet to the total temperature of the gases at the combustion-chamber inlet may be determined from the measured loss of total pressure across the combustion chamber an… more
Date: March 3, 1947
Creator: Pinkel, I. Irving
Item Type: Refine your search to only Report
open access

The effect of high solidity on propeller characteristics at high forward speeds from wind-tunnel tests of the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 two-blade propellers

Description: From Summary: "Tests of two-blade propellers having the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 blade designs (blade activity factors of 179 and 263, respectively) have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 70 degrees for free-stream Mach numbers from 0.165 to 0.725 to determine the effects of high solidity and compressibility on propeller characteristics. The tests are part of a general investigation of propellers at high forwar… more
Date: February 27, 1947
Creator: Delano, James B.
Item Type: Refine your search to only Report
open access

Lateral Stability Characteristics of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Description: "The XF-12 airplane is a high-performance photo-reconnaissance aircraft designed for the Army Air Forces by the Republic Aviation Corporation. An investigation of a 1/8.33 - scale powered model was made in the Langley l9-foot pressure tunnel to obtain information relative to the aerodynamic design of the airplane. The model was tested with and without the original vertical tail. and with two revised tails. For the revised tail no. 1, the span of the original vertical .tail was increased about 1… more
Date: February 27, 1947
Creator: Pepper, Edward & Foster, Gerald V.
Item Type: Refine your search to only Report
open access

Minimum Specific Fuel Consumption of a Liquid-Cooled Multicylinder Aircraft Engine as Affected by Compression Ratio and Engine Operating Conditions

Description: From Summary: "An investigation was conducted on a 12-cylinder V-type liquid-cooled aircraft engine of 1710-cubic-inch displacement to determine the minimum specific fuel consumption at constant cruising engine speed and compression ratios of 6.65, 7.93, and 9.68. At each compression ratio, the effect.of the following variables was investigated at manifold pressures of 28, 34, 40, and 50 inches of mercury absolute: temperature of the inlet-air to the auxiliary-stage supercharger, fuel-air ratio… more
Date: February 26, 1947
Creator: Brun, Rinaldo J.; Feder, Melvin S. & Harries, Myron L.
Item Type: Refine your search to only Report
open access

Drag characteristics of rectangular and swept-back NACA 65-009 airfoils having aspect ratios of 1.5 and 2.7 as determined by flight tests at supersonic speeds

Description: Report presenting tests to determine the effects of sweepback angle and aspect ratio on the drag of an NACA 65-009 airfoil at supersonic speeds. The results indicated that for the range of Mach numbers investigated, increasing the sweepback angle and decreasing the aspect ratio reduced the value of the wing drag coefficient.
Date: February 24, 1947
Creator: Alexander, Sidney R. & Katz, Ellis
Item Type: Refine your search to only Report
open access

Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio: Wings Swept Behind the Mach Lines

Description: "On the basis of a recently developed theory for finite sweptback wings at supersonic speeds, calculations of the supersonic wave drag at zero lift were made for a series of wings having thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios. The results are presented in a unified form so that a single chart permits the direct determination of the wave drag for this family of airfoils for an extensive range of aspect ratio and sweepback an… more
Date: February 21, 1947
Creator: Harmon, Sidney M. & Swanson, Margaret D.
Item Type: Refine your search to only Report
open access

Investigation of High-Performance Fuels in Multicylinder and in Single-Cylinder Engines at High and Cruising Engine Speeds

Description: "An investigation was conducted to compare the knock-limited performance of a 20-percent triptane blend in 28-K fuel with that of 28-R and 33-R fuels at high engine speeds, cruising speeds, and two compression ratios in an K-1830-94 multicylinder engine. Data were obtained with the standard compression ratio of 6.7 and with a compression ratio of 3.0. The three fuels were investigated at engine speeds of 1800, 2250, 2600, and 2800 rpm at high and low blower ratios" (p. 1).
Date: February 21, 1947
Creator: Bell, Arthur H.; Nelson, R. Lee & Richard, Paul H.
Item Type: Refine your search to only Report
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Preliminary Tests at Supersonic Speeds of Triangular and Swept-Back Wings

Description: Report presenting testing of a series of thin, triangular plan-form wings, including eight triangular wings of vertex angles and three swept-back wings with circular-arc sections. Results regarding lift, center of pressure, and ideal operation of different types of wings are provided.
Date: February 21, 1947
Creator: Ellis, Macon C., Jr. & Hasel, Lowell E.
Item Type: Refine your search to only Report
open access

Drag Measurements of a 34 Degree Swept-Forward and Swept-Back NACA 65-009 Airfoil of Aspect Ratio 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report presenting the results of flight testing to determine the zero-lift drag of an NACA 65-009 airfoil at a specified aspect ratio. The results are compared to previous testing of unswept and swept-back arrangements. The swept-forward and swept-back airfoils were found to produce lower values of zero-drag lift than the unswept airfoil.
Date: February 20, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
open access

An Analytical Investigation of the Heat Losses from a U.S. Navy K-Type Airship

Description: From Summary: "The heat losses from the envelope surface of a U.S. Navy K-type airship are evaluated to determine if the use of heat is a feasible means of preventing ice and snow accumulations on lighter-than-air craft during flight and when moored uncovered. Consideration is given to heat losses in clear air (no liquid water present in the atmosphere) and in probable conditions of icing and snow. The results of the analysis indicate that the amount of heat required in flight to raise the surf… more
Date: February 17, 1947
Creator: Hillendahl, Wesley H. & George, Ralph E.
Item Type: Refine your search to only Report
open access

Tank Tests of 1/5.5-Scale Forward Dynamic Model of the Columbia XJL-1 Amphibian - Langley Tank Model 208, TED No. NACA 2336

Description: Tests of a powered dynamic model of the Columbia XJL-1 amphibian were made in Langley tank no.1 to determine the hydrodynamic stability and spray characteristics of the basic hull and to investigate the effects of modifications on these characteristics. Modifications to the forebody chime flare, the step, and the afterbody, and an increase in the angle of incidence of the wing were included in the test program. The seaworthiness and spray characteristics were studied from simulated taxi runs in… more
Date: February 17, 1947
Creator: Havens, Robert F.
Item Type: Refine your search to only Report
open access

Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Description: Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps i… more
Date: February 14, 1947
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
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