You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
Two-dimensional wind-tunnel investigation of spoiler aileron flap model for the Hughes XF-11 airplane

Two-dimensional wind-tunnel investigation of spoiler aileron flap model for the Hughes XF-11 airplane

Date: April 1, 1945
Creator: Fullmer, Felicien F , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two-dimensional wind-tunnel investigation of two NACA low-drag airfoil sections equipped with slotted flaps and a plain NACA low-drag airfoil section for XF6U-l airplane

Two-dimensional wind-tunnel investigation of two NACA low-drag airfoil sections equipped with slotted flaps and a plain NACA low-drag airfoil section for XF6U-l airplane

Date: January 1, 1946
Creator: Rice, Fred J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of alternative propellers operating behind deflected wing flaps for the XB-36 airplane

Wind-tunnel investigation of alternative propellers operating behind deflected wing flaps for the XB-36 airplane

Date: December 1, 1945
Creator: Boxer, Emanuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Vibration-response tests of a 1/5-scale model of the Grumman F6F airplane in the Langley 16-foot high-speed tunnel

Vibration-response tests of a 1/5-scale model of the Grumman F6F airplane in the Langley 16-foot high-speed tunnel

Date: November 1, 1944
Creator: Regier, Arthur A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Spray characteristics and take-off and landing stability of several modifications of a 1/8-size model of the PBN-1 flying boat : NACA model 192

Spray characteristics and take-off and landing stability of several modifications of a 1/8-size model of the PBN-1 flying boat : NACA model 192

Date: April 1, 1945
Creator: Zeck, Howard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements

Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements

Date: February 1, 1945
Creator: Sivells, James C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 1/7-scale powered model of the Kaiser tailless airplane in the Langley full-scale tunnel

Tests of a 1/7-scale powered model of the Kaiser tailless airplane in the Langley full-scale tunnel

Date: March 1, 1946
Creator: Rickey, E A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of a rudder with a spring tab on an F6F-3 airplane (BuAer No.04776)

Flight tests of a rudder with a spring tab on an F6F-3 airplane (BuAer No.04776)

Date: March 1, 1945
Creator: Williams, Walter C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of an SB2C-3 airplane with a production and tilted propeller axis

Flight tests of an SB2C-3 airplane with a production and tilted propeller axis

Date: May 1, 1945
Creator: Goranson, R Fabian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test of 0.14-scale models of the control surfaces of Army project MX-511 in attitudes simulating spins

Test of 0.14-scale models of the control surfaces of Army project MX-511 in attitudes simulating spins

Date: April 1, 1945
Creator: Hagerman, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of a 1/5-Scale Semispan Model of the Republic XF-12 Horizontal Tail Surface

Wind-Tunnel Tests of a 1/5-Scale Semispan Model of the Republic XF-12 Horizontal Tail Surface

Date: January 1, 1945
Creator: Denaci, H. G.
Description: Wind-tunnel tests of a 1/5-scale semispan model of the Republic XF-12 horizontal tail surface equipped with an internally balanced elevator were conducted in the 6- by 6-foot test section of the Langley stability tunnel. The tests included measurements of the aerodynamic characteristics of the horizontal tail with and without a beveled trailing edge and also included measurements of the tab characteristics. The variation of the aerodynamic characteristics with boundary-layer conditions and leakage in the internal-balance chambers, measurements of the boundary-layer displacement thickness near the elevator hinge axis, and pressure distributions at the mean geometric chord were also obtained. The results showed that the hinge-moment characteristics of the elevator were critical to boundary-layer conditions and internal-balance leakage. Increasing the boundary-layer displacement thickness by use of roughness strips reduced the rate of change of elevator hinge moments with tab deflection by about 20 percent. The present horizontal tail appears to be unsatisfactory for longitudinal stability with power on, however, an increase in horizontal-tail lift effectiveness should correct this difficulty. The maneuvering stick force per unit acceleration will be extremely critical to minor variations of the elevator hinge moments if the elevator is linked directly to the stick.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail Incorporating a De-Icing Air Duct

Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail Incorporating a De-Icing Air Duct

Date: January 1, 1945
Creator: MacLachlan, Robert & Miller, Sadie M.
Description: A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage, stub horizontal tail, and a de-icing air duct was tested in the Langley stability tunnel. The investigation consisted of a study of the effects of the duct, with and without air flow, on the aerodynamic characteristics of the model. The model tested was a revision of a model previously tested in the Langley stability tunnel. The revised model differed from the original model in that it incorporated a de-icing air duct, included a dorsal fin, and had a larger stub fuselage. A comparison of data obtained form tests of the original and revised models was made. The results of the investigation indicated that the air duct had very little effect on the aerodynamic characteristics of the model. A small change occurred in the variation of rudder hinge-moment coefficient with angle of attack but it is believed that this change can be corrected by a properly applied spring tab.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail with Stub Fuselage and Stub Horizontal Tail

Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail with Stub Fuselage and Stub Horizontal Tail

Date: June 2, 1945
Creator: MacLachlan, Robert
Description: A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage and stub horizontal tail was tested in the Langley stability tunnel to determine the aerodynamic characteristics of the model, The investigation included a study of the effects of boundarylayer thickness, rudder area, and cover-plate alinement on the aerodynamic characteristics. Tuft studies were made in the vicinity of the junction of the vertical and stub horizontal tails. The results of the investigation indicated that the flow in the vicinity of the junction of the vertical and stub horizontal tails was only slightly improved by the addition of a fillet. An increase in boundary-layer thickness produced a slight decrease in rudder effectiveness. The increase in lift of the combined rudders over that of the upper rudder alone was not proportional at low deflections and was approximately proportional at high deflections to the increase in rudder area. When the balance-chamber cover plates were bowed out, the change in rudder hinge moment with rudder angle was less negative. The variation of the lift coefficient with angle of attack and the variation, at small values of angle of attack, of rudder hinge-noment coefficient with angle of attack was approximately the same for all ...
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of a Portion of a PV-2 Helicopter Rotor Blade

Wind-Tunnel Tests of a Portion of a PV-2 Helicopter Rotor Blade

Date: March 29, 1945
Creator: Kemp, William B., Jr.
Description: A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the blade. Because the tunnel wall acts as a plane of sy~try, the measured aerodynamic characteristics correspond to those of an airfoil having various angles of sweepforward and sweepback. Tests were made with the vents on the lower surface open and also with the vents sealed and the internal pressure held at -20 inches of water producing an internal pressure coefficient of -1.059. The change in contour resulting from the range of internal pressures used had very little effect on the aerodynamic characteristics of the blade. The test methods were considered to simulate inadequately the flow conditions over the rotor blade because the effects of cross flow were limited to conditions corresponding to sweep of the blade. The results indicated that this type of cross flow had only minor effects on the aerodynamic characteristics of the ...
Contributing Partner: UNT Libraries Government Documents Department
Full-scale-tunnel performance tests of the PV-2 helicopter rotor

Full-scale-tunnel performance tests of the PV-2 helicopter rotor

Date: April 1, 1945
Creator: Migotsky, Eugene
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation Tests of the Ditching Behavior of an Army B-24D Airplane and a 1/16-Size Model

Correlation Tests of the Ditching Behavior of an Army B-24D Airplane and a 1/16-Size Model

Date: January 1, 1946
Creator: Jarvis, George A. & Fisher, Lloyd J.
Description: Behaviors of both model and full-scale airplanes were ascertained by making visual observations, by recording time histories of decelerations, and by taking motion picture records of ditchings. Results are presented in form of sequence photographs and time-history curves for attitudes, vertical and horizontal displacements, and longitudinal decelerations. Time-history curves for attitudes and horizontal and vertical displacements for model and full-scale tests were in agreement; maximum longitudinal decelerations for both ditchings did not occur at same part of run; full-scale maximum deceleration was 50 percent greater.
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of modifications to improve the elevator control-force characteristics of the Curtiss SB2C-10 airplane in maneuvers

Flight investigation of modifications to improve the elevator control-force characteristics of the Curtiss SB2C-10 airplane in maneuvers

Date: April 1, 1945
Creator: Reeder, John P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of factors affecting the carburetor ram and nacelle drag of an A-26B airplane

Flight investigation of factors affecting the carburetor ram and nacelle drag of an A-26B airplane

Date: July 1, 1946
Creator: Danforth, Edward C B , III
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method for correlating the cooling data of liquid-cooled engines and its application to the Allison V-3420-11 engine

A method for correlating the cooling data of liquid-cooled engines and its application to the Allison V-3420-11 engine

Date: May 1, 1945
Creator: Hagginbothom, William K , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: October 1, 1945
Creator: Haar, Marvin I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel

Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel

Date: January 16, 1946
Creator: Teplitz, Jerome; Kayten, Gerald G. & Cancro, Patrick A.
Description: A 1/7 scale semispan model of the XB-35 airplane was tested in the Langley 10 foot pressure tunnel, primarily for the purpose of investigating the effectiveness of a leading-edge slot for alleviation of stick-fixed longitudinal instability at high angles of attack caused by early tip stalling and a device for relief of stick-free instability caused by elevon up-floating tendencies at high angles of attack. Results indicated that the slot was not adequate to provide the desired improvement in stick-fixed stability. The tab-flipper device provided improvement in stick-free stability abd two of the linkage combinations tested gave satisfactory variations of control force with airspeed for all conditions except that in which the wing-tip "pitch-control" flap was fully deflected. However, the improvement in control force characteristics was accompanied by a detrimental effect on stick-fixed stability because of the pitching moments produced by the elevon tab deflection.
Contributing Partner: UNT Libraries Government Documents Department
Correlation of engine-cooling data

Correlation of engine-cooling data

Date: January 1, 1945
Creator: Brevoort, Maurice J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) II : lateral and directional stability and control

Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) II : lateral and directional stability and control

Date: February 1, 1945
Creator: Reeder, John P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) I : longitudinal stability and control

Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) I : longitudinal stability and control

Date: February 1, 1945
Creator: Reeder, John P
Description: None
Contributing Partner: UNT Libraries Government Documents Department