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A Flight Investigation of the Ice-Prevention Requirements of the United States Naval K-Type Airship

Description: Report discussing a research program to investigate ice prevention and elimination on airships in order to develop suitable airship ice-prevention equipment. A Naval K-type airship was equipped with photographic and meteorological tools in order to record ice formation and the propellers were outfitted with electrically heated blade shoes. Testing discovered that an airship can be flown successfully in wet snow and freezing rain with only the propellers and induction systems protected from the … more
Date: October 19, 1945
Creator: Hillendahl, Wesley H.
Item Type: Refine your search to only Report
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Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage

Description: Report presenting wind-tunnel tests made to determine the aerodynamic characteristics of a scale model of a high-speed bomber with a dual pusher propeller aft of the empennage. Some of the results discussed include longitudinal, lateral, and directional stability and control, the empennage design, and ground effects on the aerodynamic characteristics. The results indicate that this particular airplane has several advantages with regard to stability and control over the conventional-type single-… more
Date: October 12, 1945
Creator: Weiberg, James A. & Schnurbusch, Alfred W.
Item Type: Refine your search to only Report
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Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 2 - Knock-Limited Charge-Air Flow and Cylinder Temperatures

Description: An investigation was conducted to correlate the knock limited performance of flight and single-cylinder engines under a variety of operating conditions.
Date: October 12, 1945
Creator: Brown, Kenneth D.; Richard, Paul H. & Wilson, Robert W.
Item Type: Refine your search to only Report
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Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine 1 - Cooling Characteristics

Description: Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differ… more
Date: October 4, 1945
Creator: Wilson, Robert W.; Richard, Paul H. & Brown, Kenneth D.
Item Type: Refine your search to only Report
open access

Endurance Tests of a 22-Inch-Diameter Pulse-Jet Engine With a Neoprene-Coated Valve Grid

Description: Report discussing the results of testing to determine the operating life of a 22-inch-diameter pulse-jet engine equipped with a neoprene-coated valve grid. The valve grid was found to extend the operating life and only reduced the performance slightly.
Date: October 3, 1945
Creator: Manganiello, Eugene J.; Valerino, Michael F. & Breisch, John H.
Item Type: Refine your search to only Report
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Sea-Level Performance Tests of a 22-Inch-Diameter Pulse-Jet Engine at Various Simulated Ram Pressures

Description: Report on sea-level performance tests of a 22-inch-diameter pulse-jet engine on a thrust stand. The tests were conducted at several ram pressures and the entire range of fuel flows that the engine can operate at. Information about the maximum-thrust operation, operating frequency, maximum combustion chamber pressures, and operating lives is provided.
Date: October 2, 1945
Creator: Manganiello, Eugene J.; Valerino, Michael F. & Essig, Robert H.
Item Type: Refine your search to only Report
open access

The effect of afterbody length of the hydrodynamic stability of a dynamic model of a flying boat: Langley tank model 134

Description: Report presenting some model tests that will be used to guide the relation of length of afterbody and depth of step. Results indicated that an increase in length of afterbody requires an accompanying increase in depth of step to maintain adequate landing stability.
Date: October 1945
Creator: Land, Norman S.
Item Type: Refine your search to only Report
open access

Flight Measurements of the Effect on Elevator Stick Forces of Stabilizer Incidence and Elevator Rib Spacing on the P-63A-1-BE Series Airplane

Description: "Flight tests were made to determine the cause and correction for the unusual stick-free instability of the original production P-63 airplane in high-speed straight flight." The rib spacing and stabilizer incidence of the original design were found to increase instability. When they were both altered, stability was improved and fabric deflection was reduced, but stick forces were not substantially altered.
Date: October 1945
Creator: Johnson, Harold I. & Mungall, Robert G.
Item Type: Refine your search to only Report
open access

An Investigation of the Ranger V-770-8 Engine Installation for the Edo XOSE-1 Airplane 2: Aerodynamics

Description: Investigations were made to determine the cowling and cooling characteristics of the Ranger V-770-8 engine installation in an observation seaplane. Final cowl configurations possessed ample engine and oil-cooler pressure drops for cooling in the critical normal-power climb condition with any of the three baffle configurations tested. The indicated critical Mach number of the cowling was found to be 0.70 as determined by the pressure on the lower lip of the inlet.
Date: October 1945
Creator: Dennard, John S. & Nichols, Mark R.
Item Type: Refine your search to only Report
open access

Some Flight Measurements on Pressure Distribution During Tail Buffeting

Description: Report presenting pressure-distribution measurements obtained from the horizontal tail surfaces of the Curtiss P-40K airplane during low-speed pull-ups to abrupt stall in which tail buffeting was experienced. The chordwise load distributions during buffeting are similar to those experienced during angle-of-attack changes. The location of the stall and frequency of stall disturbances are also described.
Date: October 1945
Creator: Boshar, John
Item Type: Refine your search to only Report
open access

Tank Tests of a Powered Dynamic Model of a Flying Boat Having an Afterbody Length-Beam Ratio of 4.7-Langley Tank Model 203C-1

Description: Report discussing the results of testing on a flying boat model with an afterbody length-beam ratio of 4.7 to determine its takeoff and landing stability and resistance characteristics.The range of stable trims was smaller than models with a conventional afterbody, but the range of stable positions for the center of gravity was about the same. Landing stability was satisfactory, and the hump resistance and trim is less than a boat with a smaller ratio.
Date: October 1945
Creator: Olson, Roland E. & Haar, Marvin I.
Item Type: Refine your search to only Report
open access

Two-Dimensional Wind-Tunnel Investigation of Six Airfoil Sections for the Wing of the Vega XP2V-1 Airplane

Description: Report discussing testing of six airfoil sections for the wing of the Vega XP2V-1 airplane in a smooth condition and with standard leading-edge roughness. Information about the lift, drag, pitching-moment characteristics, and sensitivity to roughness is provided. No airfoil was found to be superior to the others in all categories.
Date: October 1945
Creator: Fullmer, Felicien F., Jr.
Item Type: Refine your search to only Report
open access

Résumé of NACA Stability and Control Tests of the Bell P-63 Series Airplane

Description: Report on stability and control tests of the Bell P-63 series airplanes. Information about the spin characteristics, lateral control characteristics, longitudinal stability and control characteristics and directional stability and control characteristics is provided. A chronology of testing and detailed description of the airplane and its modifications are also provided.
Date: October 19, 1944
Creator: Johnson, Harold I.
Item Type: Refine your search to only Report
open access

Ditching tests with a 1/11-size model of the Army B-25 airplane in NACA tank number 2 and on an outdoor catapult

Description: Report presenting testing to determine the best way to land the B-25 airplane in calm and rough water and to determine its probable ditching performance. By landing with flaps down in a tail-down attitude at as slow a speed as possible, smooth straight landing runs will probably result in calm water. Results regarding the effect of attitude, effect of flap setting, effect of simulated damage, effect of propellers, and effect of seaway are provided.
Date: October 1944
Creator: Jarvis, George A. & Steiner, Margaret F.
Item Type: Refine your search to only Report
open access

The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine 1: Blends of Triptane and 28-R Fuel

Description: Report discussing the knock-limited performance of blends of triptane and 28-R fuel in an F-4 engine at three sets of conditions and three compression ratios. The knock limits of the triptane blends were more sensitive to compression ratio than the 28-R fuel, and the sensitivities of the blends increased as the severity of other engine conditions increased.
Date: October 1944
Creator: Alquist, Henry E. & Tower, Leonard K.
Item Type: Refine your search to only Report
open access

Flight tests of a pursuit airplane fitted with an experimental bellows-type bob weight

Description: Report presenting flight tests to determine the longitudinal stability characteristics of a pursuit airplane when flown with and without an experimental bellows-type bob weight. When the weight was installed, the stick-free static stability remained approximately constant irrespective of the shift in center of gravity resulting from a change in fuel quantity in the auxiliary fuselage fuel tank. Although the weight functioned satisfactorily, the performance could have been enhanced by the reduct… more
Date: October 1944
Creator: Spreiter, John R. & Nissen, James M.
Item Type: Refine your search to only Report
open access

The effect of altitude on bomber performance

Description: Report presenting a study devoted to the analysis of the effect of design and operating altitude on the performance of bombers. The primary emphasis is on range performance and charts are presented with range as a function of wing loading, power loading, and design altitude. Results regarding the range at maximum L/D, range at constant power, and performance charts are provided.
Date: October 1943
Creator: Hill, Paul R. & Crigler, John L.
Item Type: Refine your search to only Report
open access

Flying qualities of a twin-engine patrol airplane as estimated from wind-tunnel tests

Description: Report presenting an estimate of the flying qualities of a twin-engine patrol airplane from wind-tunnel test results in comparison with flight observations as a possible guide in determining changes which would be necessary to improve these qualities. Results regarding the longitudinal and lateral stability and control of this airplane are provided.
Date: October 1943
Creator: Stevens, Victor I., Jr.
Item Type: Refine your search to only Report
open access

Investigation of surface irregularities on an NACA 63(420)-416, a=1.0 airfoil section for the Glenn L. Martin Company design 195

Description: Report presenting the results of an investigation made in the two-dimensional low-turbulence pressure tunnel of surface irregularities on a low-drag airfoil section. The primary objective was to determine the effects of riveted and piano-hinge-type skin joints and of an aileron slot of the drag characteristics. Any type of surface irregularities at the front spar were found to cause substantial increase in drag.
Date: October 1943
Creator: Braslow, Albert L.
Item Type: Refine your search to only Report
open access

Pressure distribution measurements on various surfaces of a 0.2375-scale model of the Douglas XA-26 airplane in the 19-foot pressure tunnel

Description: Report presenting pressure-distribution measurements on a scale model of the Douglas XA-26 airplane as obtained in the 19-foot pressure tunnel. The measurements were made on the spinner-cowl-nacelle assembly and the fuselage for a range of angles of yaw and angles of attack.
Date: October 1943
Creator: Ashworth, C. Dixon
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel

Description: "The data are presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap comoinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and lower (slotted) flap" (p. 1).
Date: October 1942
Creator: Purser, Paul E. & Liddell, Robert B.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane

Description: Report presenting testing in the two-dimensional turbulence tunnel of a model of the tip section of the wing of the XP-63 airplane. Several alterations of the skirts and balance on the internal-balance aileron were tested to obtain various aerodynamic characteristics of the aileron.
Date: October 1942
Creator: Underwood, William J.
Item Type: Refine your search to only Report
open access

A Flight Investigation of the Stability of a Towed Body

Description: Report presenting flight tests to determine whether a towed body that was designed to meet certain specifications met the stability specification, which required that angular deviations in flight should be less than 1 degree. The requirement was met in flight in smooth air, but not in rough air, where the rolling motions were considerably larger.
Date: October 1942
Creator: Phillips, W. H.
Item Type: Refine your search to only Report
open access

Flight Measurements of the Rudder Control and Sideslip Characteristics of Four Vertical Tail Arrangements on the P-40 Series Airplanes

Description: Report presenting an investigation of rudder trim force change with speed and power, rudder force reversals in sideslips, and rudder positions in sideslips and straight flight of a P-40E airplane. Quantitative measurements of the items were made on three other vertical arrangements.
Date: October 1942
Creator: Johnson, Harold I. & Vensel, Joseph R.
Item Type: Refine your search to only Report
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