A | B | C | D | E | F | G | H | I | J | K | L | M | N | O | P | Q | R | S | T | |
---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
1 | CB # | Also released as | ||||||||||||||||||
2 | NACA-CB-3D24 | Study of the two-dimensional flow through a converging-diverging nozzle | ||||||||||||||||||
3 | NACA-CB-3D27 | WR-L-698 | Effects of a typical nacelle on the characteristics of a thick low-drag airfoil critically affected by leading-edge roughness | |||||||||||||||||
4 | NACA-CB-3E14 | Preliminary correlation of the effects of beveled trailing egdes on the hinge-moment characteristics of control surfaces | ||||||||||||||||||
5 | NACA-CB-3E19 | WR-W-101 | Notes on maximum airplane angular velocities | |||||||||||||||||
6 | NACA-CB-3E27 | WR-L-757 | Characteristics of an NACA 66, S-209 section hydrofoil at several depths | |||||||||||||||||
7 | NACA-CB-3E29 | WR-L-406 | Some effects of Reynolds and Mach numbers on the lift of an NACA 0012 rectangular wing in the NACA 19-foot pressure tunnel | |||||||||||||||||
8 | NACA-CB-3F17 | WR-E-116 | Effect of exhaust back pressure on engine power | |||||||||||||||||
9 | NACA-CB-3I13 | WR-L-452 | Tests in the NACA two-dimensional low-turbulence tunnel of airfoil sections designed to have small pitching moments and high lift-drag ratios | |||||||||||||||||
10 | NACA-CB-3K18 | WR-W-3 | Hood and Allen | |||||||||||||||||
11 | NACA-CB-3L02 | WR-L-281 | Limitations of lifting-line theory for estimation of aileron hinge-moment characteristics | |||||||||||||||||
12 | NACA-CB-3L07 | WR-L-338 | The advantages of uniform fuel distribution for air-cooled engines from considerations of cooling requirements and fuel economy | |||||||||||||||||
13 | NACA-CB-4A27 | Effects of interaction between normal shock and boundary layer | ||||||||||||||||||
14 | NACA-CB-4D10 | The possible use of ceramic materials in aircraft propulsion systems | ||||||||||||||||||
15 | NACA-CB-5B05 | WR-A-11 | Computation of hinge-moment characteristics of horizontal tails from section data | |||||||||||||||||
16 | NACA-CB-5H03 | A preliminary survey of existing information pertaining to dynamic loads in aircraft structures | ||||||||||||||||||
17 | NACA-CB-5H31 | WR-A-57 | Comparison of the energy method with the accelerometer method of computing drag coefficients from flight data | |||||||||||||||||
18 | NACA-CB-E5A04 | WR-E-207 | Suitability of ethers as aviation fuel components the knock-limited performance of several ethers blended with AN-F-28 fuel | |||||||||||||||||
19 | NACA-CB-E5J11 | WR-E-208 | A relation between knock-limited or preignition-limited air-fuel ratio at lean mixtures and fuel-air ratio at rich mixtures | |||||||||||||||||
20 | NACA-CB-E5K21 | WR-E-209 | The effect of two inlet-duct designs on turbine efficiency | |||||||||||||||||
21 | NACA-CB-L4D15 | Wire-strain-gage hinge-moment indicators for use in tests of airplane models | ||||||||||||||||||
22 | NACA-CB-L4E25 | WR-L-200 | A proposed method of measuring engine charge air flow in flight | |||||||||||||||||
23 | NACA-CB-L4E29 | WR-L-75 | Effect of Mach number on position error as applied to a pitot-static tube located 0.55 chord ahead of an airplane wing | |||||||||||||||||
24 | NACA-CB-L4G10 | WR-L-140 | Wind tunnel investigation of NACA 66(215)-216, 66,1-212, and 65(sub 1)-212 airfoils with 0.20-airfoil-chord split flaps | |||||||||||||||||
25 | NACA-CB-L4G17 | WR-L-141 | Investigation of effects of various camouflage paints and painting procedures on the drag characteristics of an NACA 65(sub 421)-420, a = 1.0 airfoil section | |||||||||||||||||
26 | NACA-CB-L4H01 | WR-L-24 | Effect of power on the stick-fixed neutral points of several single-engine monoplanes as determined in flight | |||||||||||||||||
27 | NACA-CB-L4H10 | WR-L-209 | Tests of the NACA 653-018 airfoil section with boundary-layer control by suction | |||||||||||||||||
28 | NACA-CB-L4H12 | WR-L-178 | Wind-tunnel investigation of aileron effectiveness of 0.20-airfoil-chord plain ailerons of true airfoil contour on NACA 65(sub 2)-415, 65(sub 3)-418 and 65(sub 4)-421 airfoil sections | |||||||||||||||||
29 | NACA-CB-L4H14 | WR-L-181 | Analysis of vertical-tail loads in rolling pull-out maneuvers | |||||||||||||||||
30 | NACA-CB-L4I25 | WR-L-156 | Aerodynamic characteristics of the NACA 747A315 and 747A415 airfoils from tests in the NACA two-dimensional low-turbulence pressure tunnel | |||||||||||||||||
31 | NACA-CB-L4I30 | WR-L-664 | Effects of trailing-edge modifications on pitching moment characteristics of airfoils | |||||||||||||||||
32 | NACA-CB-L4L07 | WR-L-182 | The relation between spanwise variations in the critical Mach number and spanwise load distributions | |||||||||||||||||
33 | NACA-CB-L5C01 | WR-L-116 | Estimation of stick-fixed neutral points of airplanes | |||||||||||||||||
34 | NACA-CB-L5C09 | WR-L-19 | Note on compressibility effects on downwash at the tail at subcritical speeds | |||||||||||||||||
35 | NACA-CB-L5E22 | WR-L-91 | Flight investigation at high speeds of flow conditions over an airplane wing as indicated by surface tufts | |||||||||||||||||
36 | NACA-CB-L5F01 | WR-L-111 | Effect of elevator-profile modifications and trailing-edge strips on elevator hinge-moment and other aerodynamic characteristics of a full-scale horizontal tail surface | |||||||||||||||||
37 | NACA-CB-L5F28 | WR-L-23 | Variation with Mach Number of Static and Total Pressures Through Various Screens | |||||||||||||||||
38 | NACA-CB-L5H01 | Tests at transonic speeds of the effectiveness of a swept-back trailing-edge flap on an airfoil having parallel flat surfaces, extreme sweepback, and low aspect ratio | ||||||||||||||||||
39 | NACA-CB-L5H08 | WR-L-40 | Flight tests of two airplanes having moderately high effective dihedral and different directional stability and control characteristics | |||||||||||||||||
40 | NACA-CB-L5H27 | WR-L-726 | Effects of external fuel tanks and bombs on critical speeds of aircraft | |||||||||||||||||
41 | NACA-CB-L5J04 | WR-L-82 | Effects of Reynolds number and leading-edge roughness on lift and drag characteristics of the NACA 653-418, a=1.0 airfoil section | |||||||||||||||||
42 | NACA-CB-L6B26 | WR-L-728 | Internal and external aerodynamics of ducted bodies at supersonic speeds | |||||||||||||||||
43 | NACA-CB-L6D08 | Total drag of a body of fineness ratio 12 and its stabilizing tail surfaces measured during free fall at transonic speeds | ||||||||||||||||||
44 | NACA-CB | WR-E-81 | Construction of finned aluminum muffs for aircraft engine cylinder barrels | |||||||||||||||||
45 | NACA-CB | WR-L-231 | Preliminary experimental investigation of airfoils in cascade | |||||||||||||||||
46 | NACA-CB | WR-L-450 | Notes on the effects of trailing-edge shapes of low-drag airfoils on profile drag and the trim and balance of control surfaces | |||||||||||||||||
47 | NACA-CB | WR-L-474 | Condensation trails : where they occur and what can be done about them | |||||||||||||||||
48 | NACA-CB | WR-L-497 | The effect of spinner-body gap on the pressures available for cooling in the NACA E-type cowling | |||||||||||||||||
49 | NACA-CB | WR-L-527 | A preliminary study of the effect of compressive load on the fairness of a low-drag wing specimen with z-section stiffeners | |||||||||||||||||
50 | NACA-CB | WR-L-659 | Investigation of extreme leading-edge roughness on thick low-drag airfoils to indicate those critical to separation | |||||||||||||||||
51 | NACA-CB | WR-L-660 | Interference effects of longitudinal flat plates on low-drag airfoils | |||||||||||||||||
52 | NACA-CB | WR-L-661 | Investigation of the variation of lift coefficient with Reynolds number at a moderate angle of attack on a low-drag airfoil | |||||||||||||||||
53 | NACA-CB | WR-L-695 | Some lift and drag measurements of a representative bomber nacelle on a low-drag wing I | |||||||||||||||||
54 | NACA-CB | WR-L-696 | Some lift and drag measurements of a representative bomber nacelle on a low-drag wing II | |||||||||||||||||
55 | NACA-CB | Angles of zero lift for some NACA low-drag airfoils | ||||||||||||||||||
56 | NACA-CB | Investigation of a low-drag gun port in the NACA two-dimensional low-turbulence tunnel | ||||||||||||||||||
57 | NACA-CB | Preliminary results of flight tests of a conventional three-blade propeller at high speeds | ||||||||||||||||||
58 | NACA-CB | Flight tests of internally balanced, sealed ailerons on the Curtiss XP-60 airplane | ||||||||||||||||||
59 | NACA-CB | Comparison of aileron control characteristics as determined in flight tests of P-36, P-40, Spitfire and Hurricane pursuit airplanes | ||||||||||||||||||
60 | NACA-CB | Langley Memorial aeronautical laboratory: British drawings of "G" restrictors and control booster | ||||||||||||||||||
61 | NACA-CB | Control-surface instability of high-speed airplanes | ||||||||||||||||||
62 | NACA-CB | Angular velocities in spins as indicated by Model tests in the NACA free spinning wind tunnels | ||||||||||||||||||
63 | NACA-CB | Progress in the investigation of condensation trails left by airplanes in flight | ||||||||||||||||||
64 | NACA-CB | Observation of condensation trails formed by XC-35, airplane over Langley Field, Va. | ||||||||||||||||||
65 | NACA-CB | Notes on prediction and elimination of exhaust type condensation trails | ||||||||||||||||||
66 | NACA-CB | NACA apparatus and methods for take-off and landing measurements | ||||||||||||||||||
67 | NACA-CB | Aileron control chacteristics as determined in flight tests of p-36, p-40, spitfire and hurricane pursuit airplanes | ||||||||||||||||||
68 | ||||||||||||||||||||
69 | ||||||||||||||||||||
70 | ||||||||||||||||||||
71 | ||||||||||||||||||||
72 | ||||||||||||||||||||
73 | ||||||||||||||||||||
74 | ||||||||||||||||||||
75 | ||||||||||||||||||||
76 | ||||||||||||||||||||
77 | ||||||||||||||||||||
78 | ||||||||||||||||||||
79 | ||||||||||||||||||||
80 | ||||||||||||||||||||
81 | ||||||||||||||||||||
82 | ||||||||||||||||||||
83 | ||||||||||||||||||||
84 | ||||||||||||||||||||
85 | ||||||||||||||||||||
86 | ||||||||||||||||||||
87 | ||||||||||||||||||||
88 | ||||||||||||||||||||
89 | ||||||||||||||||||||
90 | ||||||||||||||||||||
91 | ||||||||||||||||||||
92 | ||||||||||||||||||||
93 | ||||||||||||||||||||
94 | ||||||||||||||||||||
95 | ||||||||||||||||||||
96 | ||||||||||||||||||||
97 | ||||||||||||||||||||
98 | ||||||||||||||||||||
99 | ||||||||||||||||||||
100 |