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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
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