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An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 5: Effect of Thermal System on Airplane Cruise Performance

Description: Report presenting flight tests conducted to evaluate the effect of a thermal ice prevention system on the aerodynamic performance of a C-46 cargo airplane. The installation of the thermal ice-prevention system was found to reduce the indicated airspeed by about 6 miles per hour. Results regarding the overall performance change resulting from the installation of the thermal system, reduction of power attributed to heat-exchanger exhaust-gas back pressure, reduction of power attributed to the int… more
Date: May 1945
Creator: Selna, James
Partner: UNT Libraries Government Documents Department
open access

Some Notes on the Effects of Jet-Exit Design on Static Longitudinal Stability

Description: Report discussing several types of jet-exit designs, including normal, beveled, and unsymmetrical shapes, and their effect on the stability characteristics of the aircraft. No deviation of the jet center line from its exposed path is likely to be obtained if a jet exist is used that is normal to the flow. Having a tilted or asymmetrical exit was found to adversely affect the stability of the aircraft.
Date: May 1946
Creator: Gillis, Clarence L. & Weil, Joseph
Partner: UNT Libraries Government Documents Department
open access

Tests of the Jet-Motor Air-Intake Duct System on a 1/4-Scale Stub-Wing Model of a Pursuit-Type Airplane

Description: Report discussing the characteristics of the jet-motor air-intake duct system for a pursuit-type airplane with modifications to the duct system. Details of its effects on the Mach number, high pressure recovery, drag, and simplicity of the system are provided. Problems regarding the flow condition through the ducts and some potential modifications to prevent further issues are also described.
Date: May 1946
Creator: Hanson, Frederick H., Jr.
Partner: UNT Libraries Government Documents Department
open access

Hydraulic Characteristics of the NACA Injection Impeller

Description: Report discussing a mock-up injection impeller created to investigate the hydraulic characteristics and limitations of the NACA injection impeller currently in use. Information about the form and magnitude of critical factors of fuel-transfer leakage and peripheral fuel distribution is provided as well as the effects of design variations of components on hydraulic characteristics. Several revisions in portions of the impeller are suggested to improve its fuel-transfer, fuel-pumping, and fuel-eq… more
Date: May 1946
Creator: Ritter, William K.; Johnsen, Irving A. & Lieblein, Seymour
Partner: UNT Libraries Government Documents Department
open access

Static-Thrust Investigation of Full-Scale PV-2 Helicopter Rotors Having NACA 0012.6 and 23012.6 Airfoil Sections

Description: An investigation was conducted to compare the performance of two 25-ft-diam rotors which had identical dimensions and were similar in construction but different in blade airfoil-sections. Tests were conducted at indicated blade pitch angles from 3 degrees to 11.5 degrees and rotor speeds of 200, 290, and 371 rpm. The 23012.6 rotor required 2 percent less power to hover than the 0012.6. At thrust coefficients above design, the performance of the 23012.6 became better than the 0012.6 rotor.
Date: May 1946
Creator: Lipson, Stanley
Partner: UNT Libraries Government Documents Department
open access

Effect of Engine-Operating Variables and Internal Coolants on Spark-Advance Requirements of a Liquid-Cooled Cylinder

Description: "Tests were conducted to determine the effect of engine-operating variables and internal coolants on spark-advance requirements of a single cylinder from a 12-cylinder liquid-cooled engine for maximum take-off power and maximum cruise economy. The effects of fuel-air ratio, engine speed, air flow (charge density), mixture temperature, and internal coolants on peak-power (optimum) spark advance were investigated. In addition, tests were conducted to determine the effect of spark advance on the k… more
Date: May 18, 1945
Creator: Pfender, John F.; Dudugjian, Carl & Lietzke, A. F.
Partner: UNT Libraries Government Documents Department
open access

Relation Between Fuel Economy and Crank Angle for the Maximum Rate of Pressure Rise

Description: Report discussing an investigation to determine whether the crank angle for maximum rate of pressure rise can be used to indicate maximum-economy spark advance. Information about spark-advance tests at constant inlet-air pressure and fuel-air-ratio test results are provided.
Date: May 21, 1945
Creator: Cook, Harvey A. & Brightwell, Virginia L.
Partner: UNT Libraries Government Documents Department
open access

Cowling and Cooling Tests of a Fleetwings Model 33 Airplane in Flight

Description: Report presenting an investigation of the cooling of a Franklin 6-AC-29S horizontally opposed cylinder air-cooled engine installed in a Fleetwings model 33 trainer. The cowling on the airplane did not provide satisfactory cooling, but several alterations were tested, including with cylinder baffles. Results regarding engine cooling, aerodynamics of the cowling installation, and predicted versus actual cowling performance are provided.
Date: May 1944
Creator: Ellerbrock, Herman H., Jr. & Wilson, Herbert A., Jr.
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of an SB2C-3 Airplane With a Production and Tilted Propeller Axis

Description: Report discussing the changes in static longitudinal stability due to tilting the propeller axis of an SB2C-3 airplane downward. Tilting the propeller was found to be beneficial for stability, but only if the pilot was in a forward center-of-gravity position with a tilted engine. Installing a tilted engine reduced trim forces due to the changes in power up to 25 percent.
Date: May 1945
Creator: Goranson, R. Fabian
Partner: UNT Libraries Government Documents Department
open access

Performance Selection Charts for Gliders and Twin-Engine Tow Planes

Description: Report presenting performance charts for gliders and twin-engine tow planes with different degrees of aerodynamic and structural refinement. The glider charts display the gliding angle, useful load, stalling speeds, power required for level flight at various speeds, and power required for level flight while climbing at various speeds. The tow-plane charts show the stalling speeds, power required for level flight at various speeds, and power required for level flight while climbing at various sp… more
Date: May 1945
Creator: Ivey, H. Reese; Fitch, G. M. & Schultz, Wayne F.
Partner: UNT Libraries Government Documents Department
open access

Generalized selection charts for bombers with four 2000-horsepower engines

Description: Report presenting a study of the performance of bombers powered by four 2000-horsepower engines supercharged to 25,000 feet. A series of charts is provided with the coordinates of power loading and wing loading in order to simplify the selection of the best airplane for a given purpose.
Date: May 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Partner: UNT Libraries Government Documents Department
open access

A flight investigation of the boundary-layer characteristics and profile drag of the NACA 35-215 laminar-flow airfoil at high Reynolds numbers

Description: Report presenting testing to determine the boundary layer characteristics and profile drag of the NACA 35-215 airfoil section at high Reynolds numbers. The results indicated that a forward movement of the transition point occurred at about 3 percent of the chord due to operation of the engines and propellers.
Date: May 1941
Creator: Platt, Robert C.
Partner: UNT Libraries Government Documents Department
open access

Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Description: Report presenting tests in the two-dimensional low-turbulence pressure tunnel of a model of the NACA 66,2-116, a = 0.6 airfoil section representing the root section of the wing for the XP-63 airplane. The model was of 24-inch chord, built of wood with dural slot cover plates for the flap.
Date: May 1942
Creator: Underwood, William J. & Abbott, Frank T., Jr.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a 1/20-Scale Powered Model of a Four-Engine Transport Airplane

Description: Report presenting tests on a scale model of a four-engine transport airplane to determine the stability characteristics, empennage control-surface effectiveness, the effect of propeller rotation on longitudinal stability, and a method for carrying spare wing panels under the fuselage. The effect of two models of wing power operation on the characteristics of the model was studied. The results indicate that the model possess satisfactory stick-fixed longitudinal stability for all normal flight c… more
Date: May 30, 1944
Creator: Stevens, Victor I.; Douglass, William M. & Dods, Jules B., Jr.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Mach Number on the Aerodynamic Characteristics of a Single-Engine Pursuit Airplane as Determined From Tests of a 1/3-Scale Model

Description: Report discussing the effects of Mach number on the aerodynamic characteristics of an Allison powered single-engine pursuit airplane. Information about the lift, drag, pitching-moment characteristics, stability, tail effectiveness, and elevator effectiveness with Mach number is provided.
Date: May 3, 1945
Creator: Robinson, Robert C. & Jessen, Henry
Partner: UNT Libraries Government Documents Department
open access

Tests of Air Valves for Intermittent-Jet Engines at Speeds of 20 and 25 Cycles Per Second

Description: Report discussing a study of automatic nonreturn air valves for use in an intermittent-jet engine. Four valve-spring materials, three valve-grill materials, and five types of valves were used. Valve A, which was made out of aluminum, was found to perform the best and last the longest.
Date: May 8, 1945
Creator: Bressman, Joseph R. & McCready, Robert J.
Partner: UNT Libraries Government Documents Department
open access

A Method for Correlating the Cooling Data of Liquid-Cooled Engines and Its Application to the Allison V-3420-11 Engine

Description: Report discussing a study of the heat-transfer processes in liquid-cooled engines, an equation that has been developed based on the testing, and additional tests on an Allison V-3420-11 engine to determine the accuracy of the equation and the cooling characteristics of the engine. The equation was found to predict heat rejection to a coolant with good accuracy.
Date: May 1945
Creator: Kinghorn, George F.; Schroeder, Albert H. & Hagginbothom, William K., Jr.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Six Aromatic Amines on the Preignition-Limited Performance of 28-R Aviation Fuel in a CFR Engine

Description: Report discussing the results of testing on the suitability of six aromatic amines as fuel additives. Antiknock effectiveness, availability, physical properties, and chemical properties for knock tests were explored. The six aromatic amines were xylidines, cumidines, N-methylxylidines, N-methylcumidines, N-methylaniline, and N-methyltoluidine in 28-R aviation fuel.
Date: May 12, 1945
Creator: Male, Donald W.
Partner: UNT Libraries Government Documents Department
open access

Comparison of the Knock-Limited Performance of Triptane With 23 Other Purified Hydrocarbons

Description: "The knock-limited performance of blends containing General Motors triptane in S reference fuel and in an S plus M base fuel was determined in 17.6, F-3, F-4, and full-scale (single cylinder) engines. The results obtained are presented and are compared with published data from similar tests of 12 aromatics, 10 paraffins (including highly purified triptane), and 2 olefins. The comparison of fuels - which is based on a consideration of (a) antiknock blending sensitivity, (b) lead susceptibility, … more
Date: May 1945
Creator: Branstetter, J. Robert
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwings XBTK-1 Airplane: Longitudinal Stability and Control

Description: "An investigation was made of the static longitudinal stability, and control and stall characteristics of XBTK-1 dive bomber. Results indicate that the longitudinal stability will probably be satisfactory for all contemplated flight conditions at the rear-most CG location with elevator both fixed and free. Power effects were small. Sufficient elevator control will be available to trim in any flight condition above the ground" (p. 1).
Date: May 1945
Creator: Weil, Joseph & Boykin, Rebecca I.
Partner: UNT Libraries Government Documents Department
open access

Measurement of Flying Qualities of a DeHavilland Mosquito F-8 Airplane (AAF No. 43-334960) 1: Lateral and Directional Stability and Control Characteristics

Description: The data presented have no bearing on performance characteristics of airplane, which were considered exceptionally good in previous tests. Some of the undesirable features of lateral and directional stability and control characteristics of the F-8 are listed. Directional stability, with rudder fixed, did not sufficiently restrict aileron yaw; rudder control was inadequate during take-off and landing, and was insufficient to fly airplane with one engine; in clean condition, power of ailerons was… more
Date: May 1945
Creator: Gray, W. E., Jr.; Talmage, D. B. & Crane, H. L.
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation of NACA Submerged-Duct Entrances

Description: The results of an investigation of submerged-duct entrances are presented. It is shown that this type of entrance possesses the following characteristics: 1) very high-critical-compressibility speeds throughout the range of high-speed inlet velocity ratios; 2) very low pressure losses for the air entering the duct at all inlet-velocity ratios; and, 3) low external drag. These characteristics are obtained by the proper shaping of the contour of the upstream approach to the submerged inlets and b… more
Date: May 23, 1945
Creator: Frick, Charles W.; Davis, Wallace F.; Randall, Lauros & Mossman, Emmet A.
Partner: UNT Libraries Government Documents Department
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