Call Number (LC) Title Results
Y 3.N 21/5:6/547 Development of the N.A.C.A. slot-lip aileron / 1
Y 3.N 21/5:6/548 Flight tests of a balanced split flap with particular reference to rapid operation / 1
Y 3.N 21/5:6/549 Drag of prestone and oil radiators on the YO-31A airplane / 1
Y 3.N 21/5:6/550 Limitations of the pilot in applying forces to airplane controls /
Limitations of pilot in applying forces to airplane controls. 		2
Y 3.N 21/5:6/551 Tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise - N.A.C.A. model 35 series /
Tank tests of 3 models of flying-boat hulls of pointed℗--step type with different angles of dead rise, N. A. C. A. model 35 series. 		2
Y 3.N 21/5:6/552 Wind-tunnel tests of wing flaps suitable for direct control of glide-path angle /
Wind℗--tunnel tests of wing flaps suitable for direct control of glide-path angle. 		2
Y 3.N 21/5:6/553 Notes on the technique of landing airplanes equipped with wing flaps /
Notes on technique of landing airplanes equipped with wing flaps. 		2
Y 3.N 21/5:6/554 Circular motion of bodies of revolution /
Circular motion of bodies of revolution. 		2
Y 3.N 21/5:6/555 Piloting technique for recovery from spins /
Piloting technique for recovery from spins. 		2
Y 3.N 21/5:6/556 Further measurements of normal accelerations on racing airplanes /
Further measurements of normal accelerations on racing airplanes. 		2
Y 3.N 21/5:6/557 Considerations of the take-off problem /
Considerations of the take-off problem. 		2
Y 3.N 21/5:6/558 The performance of a DePalma Roots-type supercharger /
Performance of DePalma Root-s℗-type supercharger. 		3
Y 3.N 21/5:6/559 Combustion-engine temperatures by the sodium line-reversal method /
Combustion-engine temperatures by sodium line℗--reversal method. 		3
Y 3.N 21/5:6/560 A comparison of corrosion-resistant steel (18 percent chromium - 8 percent nickel) and aluminum alloy (24ST) /
Comparison of corrosion-resistant steel (18 percent chromium-8 percent nickel) and aluminum alloy (24ST) 		3
Y 3.N 21/5:6/561 Full-scale wind-tunnel tests to determine a satisfactory location for a service pitot-static tube on a low-wing monoplane /
Full-scale wind℗--tunnel tests to determine satisfactory location for service pitot-static tube on low-wing monoplane. 		3
Y 3.N 21/5:6/562 Remarks on elastic axis of shell wings.
Remarks on the elastic axis of shell wings / 		2
Y 3.N 21/5:6/563 Tank tests of models of floats for single-float seaplanes - first series /
Tank tests of models of floats for single-float seaplanes - First series /
Tank tests of models of floats for single-float seaplanes, 1st series. 		3
Y 3.N 21/5:6/564 Procedure for determining speed and climbing performance of airships /
Procedure for determining speed and climbing performance of airships. 		3
Y 3.N 21/5:6/565 Influence of fuel-oil temperature on the combustion in a prechamber compression-ignition engine /
Influence of fuel-oil temperature on combustion in pre-chamber compression-ignition engine. 		3
Y 3.N 21/5:6/566 Tank tests of a model of the NC flying-boat hull - N.A.C.A. Model 44 /
Tank tests of model of NC flying-boat hull, N. A. C. A. model 44. 		3