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NACA Research Memorandums
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An analysis of the forces and pressure distribution on a wing with the leading edge swept back 37.25 degrees
Longitudinal characteristics of two 47.7 degree sweptback wings with aspect ratios of 5.1 and 6.0 at Reynolds numbers up to 10 x 10(exp 6)
An NACA transonic test section with tapered slots tested at Mach numbers to 1.26
Experimental investigation of the effectiveness of various suction-slot arrangements as a means for increasing the maximum lift of the NACA 65(sub 3)-018 airfoil section
Investigation at high subsonic speeds of a 45 sweptback horizontal tail with plain and horn-balanced control surfaces
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Longitudinal Stability and Control Characteristics at a Mach Number of 1.40
Wing-flow measurements of longitudinal stability and control characteristics of a supersonic airplane configuration having a 42.8 degree sweptback circular arc wing with aspect ratio 4.0, taper ratio 0.50, and sweptback tail surfaces
The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed
Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds
Flight Investigation of the Pressure Distributions and Loads on a Front and Rear Sliding Canopy
Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor
Full-Scale Investigation of Boundary-Layer Control by Suction Through Leading-Edge Slots on a Wing-Fuselage Configuration Having 47.5 Degree Leading-Edge Sweep With and Without Flaps
Tests of a Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Stability and Control
Experimental investigation of thrust augmentation of 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures in compressor
Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures
Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers
Pressure Distributions on the Blade Sections of the NACA 10-(5)(066)-03 Propeller Under Operating Conditions
An Experimental Investigation of a Jet-Engine Nacelle in Several Positions on a 37.25 Degree Swept-Back Wing
Pressure Coefficients at Mach Numbers from 0.60 to 0.85 for a Semispan Wing with NACA 0012-64 Section, 20-Percent-Chord Plain Aileron, and 0 Degree and 45 Degree Sweepback
Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane
Effect of Various Modifications on Drag and Longitudinal Stability and Control Characteristics at Transonic Speeds of a Model of the XF7U-1 Tailless Airplane: NACA Wing-FLow Method, TED No. NACA DE 307
Maximum-Lift Investigation of a 1/40-Scale X-1 Airplane Wing at Mach Numbers From 0.60 to 1.15
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: stability and control characteristics
The Effect of Spanwise Aileron Location on the Rolling Effectiveness of Wings With 0 Degree and 45 Degree Sweep at Subsonic, Transonic, and Supersonic Speeds
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