Call Number (LC) Title Results
Y 3.N 21/5:6/614 Fuselage-drag tests in the variable-density wind tunnel : streamline bodies of revolution, fineness ratio of 5 /
Fuselage-drag tests in the variable-density wind tunnel : Streamline bodies of revolution, fineness ratio of 5. 		3
Y 3.N 21/5:6/615 Motion of the two-control airplane in rectilinear flight after initial disturbances with introduction of controls following an exponential law /
Motion of the two-control airplane in rectilinear flight after initial disturbances with introduction of controls following an exponential law.
Motion of the two-control airplane in rectilinear flight after initial disturbances with introduction of controls following the exponential law / 		3
Y 3.N 21/5:6/616 The measurement of air speed of airplanes /
The Measurement of air speed of airplanes /
The measurement of air speed of airplanes. 		3
Y 3.N 21/5:6/617 Stability of structural members under axial load.
Stability of structural members under axial load / 		3
Y 3.N 21/5:6/618 Increasing the strength of aluminum-alloy columns by prestressing /
Increasing the strength of aluminum-alloy columns by prestressing. 		3
Y 3.N 21/5:6/619 Compression-ignition engine performance at altitudes and at various air pressures and temperatures /
Compression-ignition engine performance at altitudes and at various air pressures and temperatures. 		3
Y 3.N 21/5:6/620 Energy loss, velocity distribution, and temperature distribution for a baffled cylinder model /
Energy loss, velocity distribution, and temperature distribution for a baffled cylinder model. 		3
Y 3.N 21/5:6/621 Pressure drop across finned cylinders enclosed in a jacket /
Pressure drop across finned cylinders enclosed in a jacket. 		3
Y 3.N 21/5:6/622 Flight tests of an airplane showing dependence of the maximum lift coefficient on the test conditions /
Flight tests of an airplane showing dependence of the maximum lift coefficient on the test conditions. 		3
Y 3.N 21/5:6/623 Maximum forces applied by pilots to wheel-type controls /
Maximum forces applied by pilots to wheel-type controls. 		3
Y 3.N 21/5:6/624 Performance characteristics of venturi tubes used in aircraft for operating air-driven gyroscopic instruments /
Performance characteristics of Venturi tubes used in aircraft for operating air-driven gyroscopic instruments.
Performance characteristics of venturi tubes use in aircraft for operating air-driven gyroscopic instruments / 		3
Y 3.N 21/5:6/625 Spinning characteristics of wings.
Spinning characteristics of wings IV : Changes in stagger of rectangular Clark Y biplane cellules.
Spinning characteristics of wings. : IV - Changes in stagger of rectangular Clark Y biplane cellules / 		3
Y 3.N 21/5:6/626 Static thrust analysis of the lifting airscrew /
Static thrust analysis of lifting airscrew. 		3
Y 3.N 21/5:6/627 Pressure distribution over a Clark Y-H airfoil section with a split flap /
Pressure distribution over Clark Y-H airfoil section with split flap. 		3
Y 3.N 21/5:6/628 Plastics as structural materials for aircraft /
Plasties as structural materials for aircraft. 		3
Y 3.N 21/5:6/629 A sound pressure-level meter without amplification /
Sound pressure-level meter without amplification.
A Sound pressure-level meter without amplification / 		3
Y 3.N 21/5:6/630 Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails.
Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails. : II. Mass distributed along the fuselage /
Free-spinning wind-tunnel tests of low-wing monoplane with systematic changes in wings and tails : 2. Mass distributed along fuselage. 		3
Y 3.N 21/5:6/631 Wind-tunnel tests of carburetor-intake rams /
Wind-tunnel tests of carburetor-intake rams. 		3
Y 3.N 21/5:6/632 Improvement of aileron effectiveness by the prevention of air leakage through the hinge gap as determined in flight /
Improvement of aileron effectiveness by prevention of air leakage through hinge gap as determined in flight. 		3
Y 3.N 21/5:6/633 Spinning characteristics of wings.
Spinning characteristics of wings : 5, N. A. C. A. 0009, 23018, and 6718 monoplane wings.
Spinning characteristics of wings. : V - N.A.C.A. 0009, 23018, and 6718 monoplane wings / 		3