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Flight Measurements of the Effect of Various Amounts of Aileron Droop on the Low-Speed Lateral-Control Characteristics of an Observation Airplane (open access)

Flight Measurements of the Effect of Various Amounts of Aileron Droop on the Low-Speed Lateral-Control Characteristics of an Observation Airplane

Report presenting tests of the low-speed lateral-control characteristics of an observation airplane with ailerons and spoilers in combination and with the spoilers disconnected and the ailerons used alone with various amounts of droop. The results indicated that in unstalled flight at low speeds and with flaps deflected, little or no aerodynamic benefit was derived by changing the lateral-control system from the aileron and spoiler combination to a normal aileron installation either with or without aileron droop.
Date: August 18, 1943
Creator: Turner, William N.
System: The UNT Digital Library
Effect of the Performance of a Turbosupercharged Engine of an Exhaust-Gas-to-Air Heat Exchanger for Thermal Ice Prevention (open access)

Effect of the Performance of a Turbosupercharged Engine of an Exhaust-Gas-to-Air Heat Exchanger for Thermal Ice Prevention

This report presents the results of a flight investigation to determine the effect on the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger installed between the engine-exhaust collector ring and the turbosupercharger. The background, results, and discussion of the investigation are described.
Date: August 23, 1945
Creator: Look, Bonne C.
System: The UNT Digital Library
An Investigation of Aircraft Heaters 18: A Design Manual for Exhaust Gas and Air Heat Exchangers (open access)

An Investigation of Aircraft Heaters 18: A Design Manual for Exhaust Gas and Air Heat Exchangers

Report presenting a summary of a series of reports regarding heat exchangers, and in particular, the design of exhaust gas and air heat exchangers. The four parts included are a summary of heat transfer equations, single pass heat exchangers, heater performance in flight, and appendicies with additional aerodynamic information.
Date: August 1945
Creator: Boelter, L. M. K.; Martinelli, R. C.; Romie, F. E. & Morrin, E. H.
System: The UNT Digital Library
Stresses Near the Juncture of a Closed and an Open Torsion Box as Influenced by Bulkhead Flexibility (open access)

Stresses Near the Juncture of a Closed and an Open Torsion Box as Influenced by Bulkhead Flexibility

Report discussing an open box joined to a closed box subjected to torsional loading. A stiff bulkhead and a flexible bulkhead were tested at the discontinuity and the results were compared to a previously published theory. Stress distribution was found to not be sensitive to bulkhead stiffness when the stiffness is large, but the calculations became sensitive to errors in estimating when the stiffness was small.
Date: August 1945
Creator: Kuhn, Paul & Brilmyer, Harold G.
System: The UNT Digital Library
Wind-Tunnel Investigation of Control-Surface Characteristics 3: A Small Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil (open access)

Wind-Tunnel Investigation of Control-Surface Characteristics 3: A Small Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil

Report presenting tests in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a small amount of aerodynamic balance. In the investigation, the effect of balance nose shape and gap at the nose of the flap has been determined. The results indicate that, in general, the lift effectiveness of the flap was unaffected by the addition of a small amount of aerodynamic overhang, and the balance effectiveness of the flap was increased.
Date: August 1941
Creator: Ames, Milton B., Jr.
System: The UNT Digital Library
Wind-tunnel investigation of control-surface characteristics II : a large aerodynamic balance of various nose shapes with a 30-percent-chord flap on an NACA 0009 airfoil (open access)

Wind-tunnel investigation of control-surface characteristics II : a large aerodynamic balance of various nose shapes with a 30-percent-chord flap on an NACA 0009 airfoil

Report presenting testing of an NACA 0009 airfoil with a 30-percent-chord flap with a 49.5-percent flap-chord balance with various nose shapes and two gaps. The results indicated that the flap is overbalanced when deflected, regardless of nose shape. Results regarding lift, hinge moment of flap, drag, pitching moment, and effect of differential balancing tab are provided.
Date: August 1941
Creator: Sears, Richard I. & Hoggard, H. Page, Jr.
System: The UNT Digital Library
Wind-Tunnel Investigation of a Full-Span Retractable Flap in Combination With Full-Span Plain and Internally Balanced Ailerons on a Tapered Wing (open access)

Wind-Tunnel Investigation of a Full-Span Retractable Flap in Combination With Full-Span Plain and Internally Balanced Ailerons on a Tapered Wing

Report discusses the results of an investigation into a full-span retractable flap in combination with a full-span plain and internally balanced ailerons on a tapered wing of a typical fighter airplane.The flap was designed to improve lateral control during high lifts for landing and take-off. The effects on the maximum life coefficient, aileron effectiveness, estimated rates of roll, and stick forces are provided.
Date: August 1943
Creator: Rogallo, F. M.; Lowry, John G. & Fischel, Jack
System: The UNT Digital Library
Wind-tunnel tests of spoilers on tail surfaces (open access)

Wind-tunnel tests of spoilers on tail surfaces

Report presenting wind-tunnel testing in two-dimensional and three-dimensional flow to investigate the aerodynamic characteristics of spoilers on tail surfaces for low-speed flight. Test results indicated that spoilers on tail surfaces showed little possibility of replacing conventional control surfaces. Results regarding a flap alone, rear spoiler alone, forward spoiler alone, forward spoiler and flap, and a combination of forward and rear spoilers on upper and lower surfaces in both types of flow are provided.
Date: August 1945
Creator: Liddell, Robert B.
System: The UNT Digital Library
Tests of a Linked Differential Flap System Designed to Minimize the Reduction in Effective Dihedral Caused by Power (open access)

Tests of a Linked Differential Flap System Designed to Minimize the Reduction in Effective Dihedral Caused by Power

Report discusses the results of testing on a linked differential flap system upon the effective-dihedral characteristics of an airplane scale model. The negative dihedral changes caused by power can be materially reduced or eliminated by use of a differential flap system. The static directional stability also increased with differential flap action.
Date: August 1945
Creator: Pitkin, Marvin & Schade, Robert O.
System: The UNT Digital Library
Hinge Moments of Sealed-Internal-Balance Arrangements for Control Surfaces 2: Experimental Investigation of Fabric Seals in the Presence of a Thin-Plate Overhang (open access)

Hinge Moments of Sealed-Internal-Balance Arrangements for Control Surfaces 2: Experimental Investigation of Fabric Seals in the Presence of a Thin-Plate Overhang

Report presenting tests in a seal test chamber to determine the hinge moments contributed by the fabric seal in an internal-balance arrangement employing a thin-plate overhang. The tests were performed with various widths of fabric sealing various widths of flap-nose gap, with a horizontal, a vertical, and a circular type of wing structure forward of the balance, and with various heights of balance chamber. Results regarding seal-profile photographs, desired seal-moment characteristics, experimental seal-moment characteristics, effect of the balance configuration on the seal-moment characteristics, comparison of analytical and experimental seal-moment characteristics, computation of seal-moment characteristics by the approximate method, and application of the data are provided.
Date: August 1945
Creator: Fischel, Jack
System: The UNT Digital Library
Hinge Moments of Sealed-Internal-Balance Arrangements for Control Surfaces 1: Theoretical Investigation (open access)

Hinge Moments of Sealed-Internal-Balance Arrangements for Control Surfaces 1: Theoretical Investigation

Report presenting the results of a theoretical analysis of the hinge-moment characteristics of various sealed-internal-balance arrangements for control surfaces. The results of the investigation indicated that the most nearly linear control-surface hinge-moment characteristics can probably be obtained from a flexible seal over a narrow gap, which is so installed that the motion of the seal is restricted to a region behind the point of attachment of the seal to the wing structure.
Date: August 1945
Creator: Murray, Harry E. & Erwin, Mary A.
System: The UNT Digital Library
Analysis of Vertical-Tail Loads in Rolling Pull-Out Maneuvers (open access)

Analysis of Vertical-Tail Loads in Rolling Pull-Out Maneuvers

Bulletin presenting an analysis of the vertical-tail loads to be expected as a result of abrupt aileron action in accelerated flight, as in rolls from turns or pull-outs, for example. Critical tail loads may occur in rolling pull-out maneuvers, particularly on airplanes with good ailerons and low directional stability.
Date: August 1944
Creator: Gilruth, Robert R.
System: The UNT Digital Library
Preliminary Vibration and Flutter Studies on P-47 Tail (open access)

Preliminary Vibration and Flutter Studies on P-47 Tail

Report presenting a report illustrated by photographs and vibration records on the failure of the P-47 rudder in the high-speed tunnel at a true speed of 468 miles per hour and a density corresponding to 9000 feet altitude. The fin-rudder unit was tested as being at least representative of the tail design of the P-47 airplane.
Date: August 1943
Creator: Theodorsen, Theodore
System: The UNT Digital Library
Wind Tunnel Tests of Ailerons at Various Speeds 4: Ailerons of 0.20 Airfoil Chord and True Contour With 0.35 Aileron-Chord Extreme Blunt-Nose Balance on the NACA 23012 Airfoil (open access)

Wind Tunnel Tests of Ailerons at Various Speeds 4: Ailerons of 0.20 Airfoil Chord and True Contour With 0.35 Aileron-Chord Extreme Blunt-Nose Balance on the NACA 23012 Airfoil

Report presenting tests made on an NACA 23012 airfoil fitted with a 20-percent-chord, true-contour aileron with 35-percent-chord, extreme blunt-nose balance. The primary purpose of the investigation was to determine the variation of the aerodynamic characteristics of this type of aileron with airspeed; the effect of variations of gap width and balance-nose radii was also investigated. Results regarding hinge moments, lift, and pitching-moment coefficients are provided.
Date: August 1943
Creator: Anderson, R. A.
System: The UNT Digital Library
An investigation of aircraft heaters 13: performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers (open access)

An investigation of aircraft heaters 13: performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers

Report presenting thermal and static pressure-drop performance data on three fluted-type heat exchangers. Two of the heaters used corrugated surfaces along the fluid passages and the third one was constructed with non-corrugated surfaces. Results regarding a comparison of results on the noncorrugated heater using two different air shrouds, heat transfer, isothermal static pressure drop, nonisothermal static pressure drop, and heater surface temperatures are provided.
Date: August 1943
Creator: Boelter, L. M. K.; Guibert, A. G.; Miller, M. A. & Morrin, E. H.
System: The UNT Digital Library
An Investigation of Aircraft Heaters 14: Performance of Two Finned-Type Crossflow Exhaust Gas and Air Heat Exchangers (open access)

An Investigation of Aircraft Heaters 14: Performance of Two Finned-Type Crossflow Exhaust Gas and Air Heat Exchangers

Report presenting data on the thermal performance and the static pressure drop characteristics of two finned-type exhaust gas and air heat exchangers. One heater was constructed of copper and stainless steel while the other was constructed from aluminum alloy. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.
Date: August 1944
Creator: Boelter, L. M. K.; Guibert, A. G.; Rademacher, J. M. & Sloggy, L. J. B.
System: The UNT Digital Library
High-speed drag tests of several fuselage shapes in combination with a wing (open access)

High-speed drag tests of several fuselage shapes in combination with a wing

Drag testing was conducted in the high-speed wind tunnel of 23 conditions combining six streamline shapes and three conventional cowling-fuselage bodies. All of the models were tested in combination with a wing in order to include wing-fuselage interference effects. The critical speeds of combinations tested were, in general, determined by the wing-fuselage juncture.
Date: August 1940
Creator: Draley, Eugene C.
System: The UNT Digital Library
Wind-tunnel investigation of a section of the horizontal tail surface for the Bell XP-63 airplane (open access)

Wind-tunnel investigation of a section of the horizontal tail surface for the Bell XP-63 airplane

Report presenting force tests conducted on a model of a section of the XP-63 horizontal tail surface in the 4- by 6-foot closed-throat vertical wing tunnel. The angle-of-attack range was from the negative to the positive stall for all flap deflections.
Date: August 1941
Creator: Ames, Milton B., Jr. & Hoggard, H. Page, Jr.
System: The UNT Digital Library
Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 65(Sub 3)-418, A=1.0 Airfoil Section (open access)

Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 65(Sub 3)-418, A=1.0 Airfoil Section

Wind-tunnel tests, investigating low drag wing performance in small-scale tests, showed a large increase in minimum drag coefficient, and a decrease of maximum lift coefficient occurred with decreasing Reynolds Number above certain designated values. The lift-curve slope varied up to 6% between high and low turbulence levels. Low Reynolds Number test data are unreliable for low drag airfoils either to estimate full-scale characteristics or to determine merits of airfoils for higher Reynolds numbers.
Date: August 1944
Creator: Tucker, Warren A. & Quinn, John H.
System: The UNT Digital Library
Investigation of the Boundary Layer About a Symmetrical Airfoil in a Wind Tunnel of Low Turbulence (open access)

Investigation of the Boundary Layer About a Symmetrical Airfoil in a Wind Tunnel of Low Turbulence

Report presenting a series of boundary-layer surveys over the surface of an NACA 0012 airfoil at zero lift. Results regarding the pressure distribution, laminar boundary layer, transition, turbulent boundary layer, drag, and skin friction are provided.
Date: August 1940
Creator: von Doenhoff, Albert E.
System: The UNT Digital Library
Wind-tunnel investigation of aileron effectiveness of 0.20-airfoil-chord plain ailerons of true airfoil contour on NACA 65(sub 2)-415, 65(sub 3)-418 and 65(sub 4)-421 airfoil sections (open access)

Wind-tunnel investigation of aileron effectiveness of 0.20-airfoil-chord plain ailerons of true airfoil contour on NACA 65(sub 2)-415, 65(sub 3)-418 and 65(sub 4)-421 airfoil sections

Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel to determine the aileron effectiveness of 0.20-airfoil-chord plain ailerons of true airfoil contour on three different airfoil sections. The aileron effectiveness parameter decreased very slightly with an increase in airfoil thickness. Results regarding the plain-airfoil section characteristics, aileron effectiveness, lift characteristics, and effects of airfoil thickness are provided.
Date: August 1944
Creator: Braslow, Albert L.
System: The UNT Digital Library
The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel (open access)

The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel

"The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested" (p. 1).
Date: August 1943
Creator: Campbell, John P. & Seacord, Charles L., Jr.
System: The UNT Digital Library
Effect of Variation in Diameter and Pitch of Rivets on Compressive Strength of Panels With Z-Section Stiffeners 1 - Panels With Close Stiffener Spacing That Fail by Local Buckling (open access)

Effect of Variation in Diameter and Pitch of Rivets on Compressive Strength of Panels With Z-Section Stiffeners 1 - Panels With Close Stiffener Spacing That Fail by Local Buckling

An experimental investigation is being conducted to determine the effect of varying the rivet diameter and pitch on the compressive strength of 24S-T aluminum-alloy panels with longitudinal Z-section stiffeners. The average stress at failing load for each rivet diameter, depth of countersink, and pitch of rivet is provided
Date: August 1945
Creator: Dow, Norris F. & Hickman, William A.
System: The UNT Digital Library
Tests of a Stressed-Carrying Door in Shear (open access)

Tests of a Stressed-Carrying Door in Shear

Bulletin presenting testing of a monocoque box with a stress-carrying door made and tested in torsion. The results indicate that if a stress-carrying door and its frame are made sufficiently heavy, the torsional stiffness of the box with the door can be made greater than the torsional stiffness of the box without the cut-out" (p. 1).
Date: August 1942
Creator: Gottlieb, Robert
System: The UNT Digital Library