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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: Technical Report Archive and Image Library
Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines III: Knock-Limited Performance of 33-R as Compared with a Triptane Blend and 28-R in Flight

Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines III: Knock-Limited Performance of 33-R as Compared with a Triptane Blend and 28-R in Flight

Date: August 1, 1945
Creator: Blackman, Calvin C.
Description: A comparison has been made in flight of the antiknock characteristics of 33-R fuel with that of 28-R and a triptane blent. The knock-limited performance of the three fuels - 33-R, a blend of 80 percent 28-R plus 20 percent triptane (leaded to 4.5 ml TEL/gal), and 28-R - was investigated in two modified 14-cylinder double-row radial air-cooled engines. Tests were conducted on the engines as installed in the left inboard nacelle of an airplane. A carburetor-air temperature of approximately 85 deg F was maintained. The conditions covered at an engine speed of 2250 rpm were high and low blower ratios and spark advances of 25 deg and 32 deg B.T.C. For an engine speed of 1800 rpm only the high-blower condition was investigated for both 25 deg and 32 deg spark advances. For the conditions investigated the difference between 33-R and the triptane blend was found to be slight; the performance of 33-R fuel, however, was slightly higher than that of the triptane blend in the lean region. The knock-limited power obtained with the 33-R fuel was from 14 to 28 percent higher than that of the 28-R fuel for the entire range of test conditions; the greatest improvement ...
Contributing Partner: UNT Libraries Government Documents Department
Effect of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls of a pursuit airplane equipped with a low-drag wing

Effect of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls of a pursuit airplane equipped with a low-drag wing

Date: July 6, 1945
Creator: Blair, William K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The high-speed characteristics of several flaps and spoilers on the upper surface of the horizontal stabilizer of a model of a radial-engine pursuit airplane

The high-speed characteristics of several flaps and spoilers on the upper surface of the horizontal stabilizer of a model of a radial-engine pursuit airplane

Date: January 21, 1946
Creator: Boddy, Lee E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some flight measurements on pressure distribution during tail buffeting

Some flight measurements on pressure distribution during tail buffeting

Date: October 1, 1945
Creator: Boshar, John
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
Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwings XBTK-1 Airplane : Longitudinal Stability and Control

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

Date: May 1, 1945
Creator: Boykin, Rebecca I.
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. Increasing the slotted flap deflection above 30 degrees only slightly increased the max. lift coefficient.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of the knock-limited performance of triptane with 23 other purified hydrocarbons

Comparison of the knock-limited performance of triptane with 23 other purified hydrocarbons

Date: May 1, 1945
Creator: Branstetter, J Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Endurance tests of a 22-inch-diameter pulse-jet engine with a neoprene-coated valve grid

Endurance tests of a 22-inch-diameter pulse-jet engine with a neoprene-coated valve grid

Date: October 1, 1945
Creator: Breisch, John H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited blending characteristics of benzene, toluene, mixed xylenes, and cumene in an air-cooled cylinder

Knock-limited blending characteristics of benzene, toluene, mixed xylenes, and cumene in an air-cooled cylinder

Date: February 3, 1945
Creator: Breitwieser, Roland
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of a low-loss air valve on performance of a 22-inch-diameter pulse-jet engine

The effect of a low-loss air valve on performance of a 22-inch-diameter pulse-jet engine

Date: June 12, 1946
Creator: Bressman, Joseph R
Description: None
Contributing Partner: UNT Libraries Government Documents Department