Listing Of National Advisory Committee For Aeronautics .
Description of document:Listing of National Advisory Committee for Aeronautics(NACA) technical reports designated or identified in theNational Aeronautics and Space Administration (NASA)Scientific and Technical Information (STI) database asrestricted or nonpublic, 1944-1959Requested date:17-March-2014Released date:21-April-2014Posted date:28-April-2014Source of document:NASA Langley Research Center (LaRC)Hampton, Virginia 23681LaRC FOIA OfficerMail Stop 218Email: sts generated in 20143 lists included: Documents Exempt From Export under ExportAdministration Regulations (EAR) and InternationalTraffic in Arms Regulations (ITAR) Documents Limited to NASA Use Only Documents Limited to US Government andContractor Use OnlyThe governmentattic.org web site (“the site”) is noncommercial and free to the public. The site and materialsmade available on the site, such as this file, are for reference only. The governmentattic.org web site and itsprincipals have made every effort to make this information as complete and as accurate as possible, however,there may be mistakes and omissions, both typographical and in content. The governmentattic.org web site andits principals shall have neither liability nor responsibility to any person or entity with respect to any loss ordamage caused, or alleged to have been caused, directly or indirectly, by the information provided on thegovernmentattic.org web site or in this file. The public records published on the site were obtained fromgovernment agencies using proper legal channels. Each document is identified as to the source. Any concernsabout the contents of the site should be directed to the agency originating the document inquestion. GovernmentAttic.org is not responsible for the contents of documents published on the website.
National Aeronautics andSpace Administration' .p . · Langley Research Center100 NASA RoadHampton, VA 23681-2199·;.: .April 21, 2014Ref: 14-LaRC-F-00398This is in response to your Freedom of Information Act (FOIA) request dated and received inour office on March 17, 2014. Your request was for the following information:A listing/bibliography of NA CA technical reports that are designated or identified in the STIdatabase as classified or restricted or othenvise nonpublic.Enclosed is a listing ofNACA technical reports that are designated or identified in the STIdatabase as restricted or nonpublic. The STI database does not upload classified documentsinto the system; therefore, those types of records do not exist in the STI database. You agreedto pay 35 in fees associated with the processing of your request; however, fees were less than 15 and are not being charged in accordance with 14 CFR §1206.700(i)(2). This informationis furnished under the provisions of the FOIA. If you have any questions, please contact me at757-864-4274 or by email at carissa.s.wheeler@nasa.gov.Sincerely,Carissa S. Wheeler, FOIA OfficerNASA Langley Research Center
Documents Exempt From Export under Export Administration Regulations (EAR)and International Traffic in Arms Regulations (ITAR)NACA-EAR ITAR
NACA-EAR ITARPublicationDateDocument 7G1521-Feb-5619930089065NACA-RM-L55L06Effects of Components and Various Modifications on the Drag and the Static Stability and Church, James DControl Characteristics of a 42 Degree Swept-Wing Fighter-Airplane Model at MachNumbers of 1.60 to 2.501-Nov-5719930090008NACA-RM-L57K01Some factors affecting the stability and performance characteristics of canard aircraftconfigurationsAerodynamic and hydrodynamic characteristics of a proposed supersonic multijet waterbased hydro-ski aircraft with a variable-incidence wingAerodynamic characteristics of a model of an escape capsule for a supersonic bombertype airplane at a Mach number of 2.49An exploratory investigation at Mach numbers of 2.50 and 2.87 of a canard bomber-typeconfiguration designed for supersonic cruise flightPreliminary investigation of a variable mass-flow supersonic nose inletPreliminary data at a Mach number of 2.40 of the characteristics of flap-type controlsequipped with plain overhang balancesEffects of a series of inboard plan-form modifications on the longitudinal characteristicsof two unswept wings of aspect ratio 3.5, taper ratio 0.2, and different thicknessdistributions at Mach numbers of 1.61 and 2.01Spearman, M Leroy; Driver, , William W; Hasson, Dennis F; Spooner, Stanley H23-Oct-5719930089748NACA-RM-L57G05Presnell, John G , Jr3-Dec-5719930089951NACA-RM-L57I17Kelly, Thomas C; Carmel, Melvin M; Gregory, Donald T15-Apr-5819930090020NACA-RM-L58B28Hayes, ClydeMueller, James N; Czarnecki, K J11NACA-RM-L52F10Sevier, John R , estigation of Static Stability and Drag Characteristics of a 1/10-Scale Model of the Avco Church, James D.; Sista, Lawrence M.Booster Vehicle at Mach Numbers of 1.60 and 2.00, Coord. No. AF-AM-58Investigation of the aerodynamic characteristics of a model of a supersonic bomberconfiguration with a swept and an unswept wing at Mach numbers from 1.79 to 2.67Silvers, H Norman; Zedekar, Raymond LAn investigation of the performance of a semielliptical scoop inlet at Mach numbers ofHayes, Clyde; Mackley, Ernest A1.60, 1.76, and 2.02Investigation of aerodynamic characteristics in pitch and sideslip of a 45 degreeSpearman, M Leroy; Driver, Corneliussweptback-wing airplane model with various vertical locations of wing and horizontal tail :static longitudinal stability and control, M 2.01Investigation of flutter characteristics of three low-aspect-ratio all-movable half-spanMorgan, Homer G; Figge, Irving E; Presnell, John G , Jrcontrol surfaces at Mach numbers from 1.49 to 2.87Aerodynamic characteristics at Mach number of 2.01 of two cruciform missileSpearman, M Leroy; Robinson, Ross Bconfigurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7with several canard controlsEffects of wing sweep, horizontal-tail configuration, and a ventral fin on static stabilitycharacteristics of a model with a wing of aspect ratio 3 at Mach numbers from 2.29 to4.65Jaquet, Byron M; Fournier, Roger HPage 1 of 2 PagesReport/Patent Number
NACA-EAR ITARTitleAuthorAN INVESTIGATION OF THE PERFORMANCE OF A SEMIELLIPTICAL SCOOP INLET AT MACH Hayes, C.; Mackley, E. A.NUMBERS OF 1.60, 1.76, AND 2.02Effects of Components and Various Modifications on the Drag and the Static Stability and Church, J. D.Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbersof 1.60 to 2.50PublicationDateDocument 24813NACA-RM-L57K01Report/Patent NumberInvestigation of Drag and Static Longitudinal and Lateral Stability Characteristics of aModel of a 40.4 Deg Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06Carmel, M. M.; Turner, K. L.18-Jan-5719660010451NACA-RM-L56I17AInvestigation of flutter characteristics of three low-aspect-ratio all-movable half-spancontrol surfaces at Mach numbers from 1.49 to 2.87Figge, I. E.; Morgan, H. G.; Presnell, J. G., Jr.2-May-5819660030329NACA-RM-L58B20Page 2 of 2 Pages
Documents Limited to NASA Use OnlyNACA-NASA Limited
NACA-NASA LimitedPublicationDateDocument IDCooling Characteristics of the Allison V-1710-81 Engine . Part 1; Cylinder TemperaturesManganiello, Eugene J.; Stalder, Jackson R.; Povolny, Johnand Coolant-Flow Distribution at Typical Operating Conditions with Ethylene Glycol as the H.Coolant16-Dec-4420140001497NACA-MR-E4L16Tests of an Aftercooler for the Allison V-1710 Engine for Use in the P-63 AirplaneCooling Characteristics of the Allison V-1710-81 Engine . Part 2; Effect of CoolantConditions of Cylinder Temperatures and Cooland and Oil Heat RejectionsEstimated Altitude Performance of the Two-scale Allison V-1710 Engine with NACAAftercoolers for the P-63 AirplaneCooling Characteristics of the Allison V-1710-81 Engine. Part 3; The Effect of Oil-inletTemperature on Oil and Coolant Heat Rejection at Two Coolant Temperatures and forSeveral Engine PowersLundin, Bruce T.; Povolny, John H.; Chelko, Louis J.Manganiello, Eugene J.; Stalder, Jackson R.; Povolny, JohnH.Manganiello, Eugene J.; Stalder, Jackson R.; Lundin, Bruce 0Manganiello, Eugene J.; Stalder, Jackson R.; Lundin, Bruce T.25-Jan-4520140001495NACA-MR-E5A25aCooling Characateristics of the Allison V-1710-81 Engine. V; Preliminary Correlation ofCylinder-Head TemperaturesDetermination of Drag of Man-Carrying Parachutes in the Ames 40- by 80- Foot WindTunnelFlight and Test-Stand Investigation of High-Performance Fuels in Pratt and Whitney R1830-90C and R-1830-94 Engines. 2; Comparison of Flight R-1830-90C and R-1830-94EnginesManganiello, Eugene J.; Lundin, Bruce T.; Povolny, John H.1-Jan-4620140001150NACA-MR-E6B27Chausse, Ronald H.28-Jul-4520140001144NACA-MR-A5G28Pragliola, Phlip C.6-Nov-4520140000867NACA-MR-E5K06Investigation of the Mixture Distribution of the Wright R-3350-21 Engine and its Effect on Wilcox, Fred A.; Wallner, Lewis E.Cylinder-Head TemperaturesA Study of Preignition as a Cause of Backfiring in an Allison V-170-99 EngineBerguson, Howard E.; Harries, Myron L.; Brun, Rinaldo J.17-May-4520140000828NACA MR No. E5E176-May-4520140000868NACA-MR-E5E06Description of a Skinner Two-Stroke-Cycle Spark-Ignition Slide-Valve Engine and Results of Foster, Hampton H.; Sather, Bernard I.; Catlin, John C.Initial TestThe Effect of a Change in Compression Ratio from 6.65 to 6.0 on the Performance of anBerguson, Howard E.; Harries, Myron L.; Brun, Rinaldo J.Allison V-1710-99 EngineMethods of Reducing Failures in the Exhaust Port of the Wright R-33550 CylinderPeters, Max D.; MacGregor, Charles A.; Eckhardt, R. 0864NACA-MR-E5E06a22-May-4520140000826NACA MR-E5E22Effects of Sweep and Dihedral on Stalling and Lateral Characteristics of the Wing-Fuselage Jerome TeplitzCombination of a Model of the XA-26 Airplane with Partial and Full Span Flaps1-May-4420130014546NACA ACR No. L4E20Dynamic Characteristics of MX-570 (Model B) Autopilot as Determined from OscillatingTable TestsInvestigation of Stability and Control Characteristics of a 1/2-Scale Model of an NACAConfiguration for Guided Missiles (MX-570) in the Langley Free-Flight Tunnel, gle, Ellwyn E.Paulson, John W.; Johnson, Joseph L.; Schade, Robert O.Page 1 of 3 PagesReport/Patent Number
NACA-NASA LimitedPublicationDateDocument IDSeacord, Charles L., L6B13aNACA-MR-L6C09Seacord, Charles L., Jr.Paulson, John W.; Schade, Robert O.; Johnson, Joseph 5H29aNACA MR-L5I041-Jan-4720100039437NACA RM No. L7E221-Mar-4224-Oct-422010002115920100021160NACA Misc. Paper No. 47NACA MR Oct 24 421-Jun-4620100011251NACA-ARR-E6E14, ation of the I-40 Jet-Propulsion Engine in the Cleveland Altitude Wind Tunnel. IV - Hensley, Reece V.Analysis of Combustion-Chamber PerformanceHydrodynamic Characteristics of a 1/10-Size Powered Dynamic Model of the XP5Y-1Olson, Roland E.; Haar, Marvin I.; Woodward, David R.Flying Boat in Smooth Water: Langley Tank Model 228C-1, TED No. NACA 0029425NACA-RM-L7E28Free-Spinning Tunnel Tests of a 1/25-Scale Model of the North American XFJ-1 Airplane,TED No. NACA 2400Wing-Operation Tests of the Chance-Vought F4U-1D Airplane in the Langley Full-ScaleTunnel, TED No. NACA 2371Free-Spinning-Tunnel Tests of a 1/20-Scale Model of the Northrop N-9M AirplaneBerman, Theodore18-Nov-4620050019641NACA-RM-L6H29Prince, William R.27-Jan-4720050019475NACA-RM-L6H26MacDougall, George F., Jr.; Lichtenstein, Jacob H.4-Nov-4620050019257NACA-RM-L6G30Heat Transfer to Surfaces and Protuberances in a Supersonic Turbulent Boundary LayerBurbank, Paige B; Strass, H s of Flights Tests of MX-570 (Model B-Four-Wing Tiamat)Correlation of the Computed Rolling Motion of the MX-570 (Tiamat-Model B) GuidedMissile with that Obtained in FlightResults of First Flight Test of MX-570 TiamatInvestigation of Stability and Control Characteristics of a 1/2-Scale Model of an NACAConfiguration for Guided Missiles (MX-570) in the Langley Free-Flight Tunnel, I-Three-FinArrangementAuthorInvestigation in the Langley 19-foot Pressure Tunnel of Two Wings of NACA 65-210 and 64- Sivells, James C.; Spooner, Stanley H.210 Airfoil Sections with Various Type FlapsA Method for the Dynamic Calibration of AccelerometersHootman, James A.Memorandum Report for the Army Air Forces, Materiel Command Tests of A 0.12-Scale Delano, James B.; Mattson, Axel T.Model of the XB-33 Airplane in the 8-Foot High-Speed TunnelPerformance Charts for a Jet-Propulsion System Consisting of Compressor, a Combustion Pinkel, Benjamin; Karp, Irving M.Chamber, and a TurbineStatic Tests of a Shrouded and an Unshrouded Propeller for Navy-Westinghouse GasPlatt, Robert J., Jr.Turbine Drive. TED No. NACA 042Flying Qualities of the Curtiss XF15X-1 Airplane with a T-Tail as Estimated from WindChristiani, R. DuaneTunnel Tests of a 01.14-Scale ModelInvestigation of the Performance of the Thermal Ice-Prevention System Installed in aJukoff, David; Look, Bonne C.Douglas BTD-1 Airplane (TED No. NACA 2502)Simulated Altitude Performance of Combustors for the 9.5 Jet Engine. 2; 9.5B Combustor Bogart, DonaldPage 2 of 3 PagesReport/Patent Number
NACA-NASA LimitedTitleAuthorPublicationDateDocument IDReport/Patent NumberCorrelation of Physical Properties of Ceramic Materials with Resistance to Fracture byThermal ShockExperimental Convective Heat Transfer to a 4-Inch and 6-Inch Hemisphere at MachNumbers from 1.62 to 3.04Investigation of the Static Lateral Stability and Aileron Characteristics of a 0.067-ScaleModel of the Bell X-2 Airplane at Mach Numbers of 2.29, 2.78, 3.22, and 3.71Lidman, W G; Bobrowsky, A R1-Jul-4919930082596NACA-TN-1918Chauvin, Leo T; Maloney, Joseph P3-Feb-5419930088132NACA-RM-L53L10aFournier, Roger H.; Silvers, H. ion of a one-fifth scale model of a proposed high-submerged-speed submarinein the Langley full-scale tunnel /U/NACA Conference on Engine Stall and SurgeCocke, B. W.; Lipson, S.; Scallion, W. 79175NACA-TM-X-67600Page 3 of 3 Pages
Documents Limited to US Government and Contractor Use OnlyNACA-Limited to USG&C per 2013 NTRS Review
NACA-Limited to USG per 2013 NTRS ReviewTitleAuthorPublicationDateDocument IDReport/Patent NumberAerodynamic Load Measurements Over Leading-Edge and Trailing-Edge Plain Flaps on a 6Percent Thick Symmetrical Circular-Arc Airfoil SectionOn the Application of the Energy Method to Stability ProblemsThe Monoplane as a Lifting Vortex SurfaceWind-Tunnel Measurements on the Henschel Missile "Zitterrochen" inSubsonic and Supersonic VelocitiesCones in Supersonic FlowOn Landing Gear StressesOn the Theory of Anisotropic Shallow ShellsOn the Theory of Thin Shallow ShellsSafeguards Against Flutter of AirplanesSimulated Altitude Performance of Combustor of Westinghouse 19XB-1 Jet-PropulsionEngineCooling of Gas Turbines, IV - Calculated Temperature Distribution in the Trailing Part of aTurbine Blade Using Direct Liquid CoolingWind-Tunnel Tests at Low Speed of Swept and Yawed Wings Having Various Plan FormsUnderwood, William J.; Nuber, Robert J.22-Oct-4720110012680NACA-RML7H04Marguerre, KarlBlenk, HermannWeber; 20030067831NACA-TM-1138NACA-TM-1111NACA-TM-1159, DLUM-3122Hantzsche, W.; Wendt, H.Gentric, A.Ambartsumyan, S. A.Nazarov, A. A.deVries, GerhardChilds, J. Howard; McCafferty, Richard 424NACA-TM-1426NACA-TM-1423NACA-RM-E8J29Brown, W. Byron; Monroe, William R.18-Apr-4720030065144NACA-RM-E7B11dPurser, Paul E.; Spearman, M. y Gas Flow in Thin Pipes of Variable Cross SectionThe Effect on the Sperry Directional Gyro in TurningTests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA WingFlow MethodGas-Dynamic Investigations of the Pulse-Jet Tube. Parts 1 and 2The Load Distribution in Bolted or Riveted Joints in Light-Alloy StructuresAdaptation of combustion principles to aircraft propulsion. volume ii - combustion in airbreathing jet enginesThe prospects for laminar flow on hypersonic airplanesAn Analytical Study of Heat Requirements for Icing Protection of RadomesComponent performance investigation of J71 experimental turbine. IV-Effect of firststator adjustment; over-all performance of J71-97 turbine with 132-percent-design statorareaGuderley, G.RosselliDelTurco, RosselloAdams, Richard E.; Silsby, Norman hultz-Grunow, F.Vogt, F.Barnett, H. C.; Hibbard, R. 670095382NACA-TM-1131-Pt-1/2, Rept-2015/1-Pt-1/2NACA-TM-1135, SME-3300NACA-RM-E55G28Seiff, AlvinLewis, James PDavison, Elmer H; Petrash, Donald A; Schum, Harold 19930094386NACA-RM-A58D25NACA-RM-E53A22NACA RM E55H09The theory of plasticity in the case of simple loading accompanied by strain-hardeningIlyushin, A A1-Feb-4919930094862NACA-TM-1207Pressure recovery, drag, and subcritical stability characteristics of conical supersonicdiffusers with boundary-layer removalComparison of turbojet-engine altitude performance characteristics and ignition limitswith MIL-F-5624A fuel, grades JP-3 and JP-4Obey, Leonard T; Englert, Gerald W; Nussdorfer, Theodore J, JrBraithwaite, Willis M; Renas, Paul 94391NACA RM-E51L05Page 1 of 497 Pages
NACA-Limited to USG per 2013 NTRS ReviewTitleNACA Conference on Aircraft Loads. [A Compilation of the Papers PresentedFuel characteristics pertinent to the design of aircraft fuel systemsDynamic response at altitude of a turbojet engine with variable area exhaust nozzleAuthorBarnett, Henry C; Hibbard, R RDelio, Gene J; Rosenweig, SolomonGeneralization of turbojet and turbine-propeller engine performance in windmillingWallner, Ewis E; Welna, Henry JconditionNACA Conference on high-speed aerodynamicsNACA Conference on Aircraft Structures. [A Compilation of the Papers PResentedNACA Conference on aerodynamics of high-speed aircraftAdaptation of Combustion Principles to Aircraft Propulsion. Volume 2; Combustion in Air- Barnett, Henry C. (Editor); Hibbard, Robert R. (Editor)Breathing Jet EnginesLaboratory investigation of icing in the carburetor and supercharger inlet elbow of anZlotowski, E Eaircraft engine IV : effect of throttle design and method of throttle operation on inductionsystem icing characteristicsPublicationDateDocument -CONF-1951NACA-CONF-1955NASA-TM-110456, NACA-RM-E55G28, NAS1.15:110456NACA-WR-E-173, NACA-MR-E5L27Report/Patent NumberTwo-dimensional wind-tunnel investigation of two NACA low-drag airfoil sectionsequipped with slotted flaps and a plain NACA low-drag airfoil section for XF6U-l airplaneRice, Fred J , Jr1-Jan-4619930092789NACA-WR-L-746, NACA-MR-L5L11Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotorbladesCorrelation of mixture temperature data obtained from bare intake-manifoldthermocouplesCritical Mach Numbers of Thin Airfoil Sections with Plain FlapsAn evaluation of the knock-limited performance of triptaneAerodynamic data for a wing section of the Republic XF-12 airplane equipped with adouble slotted flapModel ditching investigations of three airplanes equipped with hydro-skisEffect of fuel density and heating value on ram-jet airplane rangeWind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane atMach Numbers of 1.45 and 1.90A theory for stability and buzz pulsation amplitude in ram jets and an experimentalinvestigation including scale effectsSome measurements of the buffet region of a swept-wing research airplane during flightto supersonic Mach numbersLow-speed investigation of the aerodynamic, control, and hinge-moment characteristicsof two types of controls on a delta-wing-fuselage model with and without nacellesRice, Fred J , Jr1-Feb-4619930092781NACA-WR-L-29, NACA-RB-L5K02White, H. Jack; Gammon, Goldie L1-Jan-4619930093118NACA-WR-E-273, NACA-MR-E5L03Pardee, Otway O'm.; Heaslet, Max A.Barnett, Henry CCahill, Jones 30092826NACA-WR-W-2, NACA-ACR-6A30NACA-WR-E-276, NACA-MR-E6B20NACA-WR-L-544, NACA-MR-L6A08AFisher, Lloyd JHenneberry, Hugh MSmith, Willard 53C17Trimpi, Robert L15-Oct-5319930087782NACA-RM-L53G28Baker, Thomas F28-May-5319930087799NACA-RM-L53D06Scallion, William I20-May-5319930087783NACA-RM-L53C18Page 2 of 497 Pages
NACA-Limited to USG per 2013 NTRS ReviewPublicationDateDocument 4A156-Oct-5319930087784NACA-RM-L53G29Measurements obtained during the glide-flight program of the Bell X-2 research airplane Day, Richard E30-Jul-5319930087801NACA-RM-L53G03aAn empirical equation for the coefficient of heat transfer to a flat surface from a planeheated-air jet directed tangentially to the surfaceWind-tunnel investigation at low speed of pitching derivatives of a 0.085-scale model ofthe Chance Vought XF8U-1 airplane : TED No. NACA DE 392Damping-in-pitch characteristics at high subsonic and transonic speeds of four 35 degreesweptback wingsTransonic flight measurement of the aerodynamic load on the extended slat of theDouglas D-558-II research airplaneAnalysis of turbine stator adjustment required for compressor design-point operation inhigh Mach number supersonic turbojet enginesAn evaluation of an aeromechanical method of minimizing servo- missile transfer functionvariations with flight conditionInteraction of bearing and tensile loads on creep properties of jointsEvaluation of several adhesives and processes for bonding sandwich constructions ofaluminum facings on paper honeycomb corePreliminary investigation of pumping and thrust characteristics of full-size cooling-airejectors at several exhaust-gas temperaturesInvestigation at Mach numbers 1.5 and 1.7 of twin-duct side air-intake system with 9degree compression ramp including modifications to boundary-layer-removal wedges andeffects of a bypass systemZerbe, John; Selna, James1-Jun-4619930090633NACA-TN-1070Jaquet, Byron M; Williams, James L1-Jan-5419930088137NACA-RM-SL54B05aKemp, William B , Jr; Becht, Robert E16-Oct-5319930087785NACA-RM-L53G29aPeele, James R27-Aug-5319930087819NACA-RM-L53F29English, Robert E; Cavicchi, Richard H9-Oct-5319930087802NACA-RM-E53G06Nason, Martin L18-Apr-5619930089184NACA-RM-L56A31Bodine, E G; Carlson, R L; Manning, G KEickner, H 8NACA-TN-2106Greathouse, W K9-Apr-5419930088138NACA-RM-E54A18Obery, Leonard J; Stitt, Leonard E12-Oct-5319930087786NACA-RM-E53H04Wind-tunnel investigation of the vortex wake and downwash field behind triangularwings and wing-body combinations at supersonic speedsExperimental investigation of the effects of plan-form taper on the aerodynamiccharacteristics of symmetrical unswept wings of varying aspect ratioSpahr, J Richard; Dickey, Robert R25-Jun-5319930087820NACA-RM-A53D10Allen, Edwin stigation at a Mach number of 1.90 of a diverter-type boundary-layer removal system Kochendorfer, Fred Dfor a scoop inletStability and control characteristics at low speed of a modified 1/10-scale model of theLockwood, Vernard E; Solomon, MartinMX-1554A designTransonic wind-tunnel investigation of the effects of taper ratio, body indentation, fixed Morgan, Francis G , Jr; Carmel, Melvin Mtransition, and afterbody shape on the aerodynamic characteristics of a 45 degreesweptback wing-body combinationFlight investigation at Mach numbers from 0.67 to 1.81 of the longitudinal stability andcontrol characteristics of a 60 degree delta-wing missile configuration having an allmovable tailMoul, Martin T; Baber, Hal T , JrPage 3 of 497 PagesReport/Patent Number
NACA-Limited to USG per 2013 NTRS ReviewTitleAuthorPublicationDateDocument IDReport/Patent NumberPreliminary investigation of the total-pressure-recovery characteristics of a symmetricand asymmetric nose inlet over a wide range of angle of attack at supersonic MachnumbersCarter, Howard S; Merlet, Charles F9-Dec-5319930087939NACA-RM-L53J30The effects of blowing over various trailing-edge flaps on an NACA 0006 airfoil section,comparisons with various types of flaps on other airfoil sections, and an analysis of flowand power relationships for blowing systemsDods, Jules B , Jr; Watson, Earl C12-Jun-5619930089185NACA-RM-A56C01An investigation at low speed of the flow over a simulated flat plate at small angles ofattack using pitot-static and hot-wire probesFlame quenching by a variable-width rectangular-slot burner as a function of pressure forvarious propane-oxygen-nitrogen mixturesExperimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressorstage designed for 40 pounds per second per unit frontal areaCorrelation of tensile strength, tensile ductility, and notch tensile strength with thestrength of rotating disks of several designs in the range of low and intermediate ductilityGault, Donald E1-Mar-5719930084689NACA-TN-3876Berlad, Abraham L28-Jan-5419930090635NACA-RM-E53K30Cullom, Richard R; Montgomery, John C; Yasaki, Paul T4-Sep-5819930090120NACA-RM-E58D04aHolms, Arthur G; Repko, Andrew J1-Sep-5219930083474NACA-TN-2791Investigation at high subsonic speeds of finned and unfinned bodies mounted at variouslocations from the wings of unswept- and swept-wing--fuselage models, includingmeasurements of body loadsSilvers, H Norman; Alford, William J1-Apr-5419930088139NACA-RM-L54B18Low-speed cascade tests of two 45 degree swept compressor blades with constantspanwise loadingThe aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45degree sweptback, aspect-ratio-4 tail deflected about a skewed hinge axis and equippedwith an inset unbalancing tabBeatty, Loren A; Savage, Melvyn; Emery, James C15-Mar-5419930088156NACA-RM-L53L07Watson, James M29-Sep-5319930087787NACA-RM-L53H13Criticality survey of hydroxides as coolant moderators for aircraft nuclear reactorsBogart, Donald; Soffer, Leonard27-Oct-5319930087821NACA-RM-E53F30Charts giving critical compressive stress of continuous flat sheet divided intoparallelogram-shaped panelsResults of measurements of maximum lift and buffeting intensities obtained during flightinvestigation of the Northrop X-4 research airplaneA compilation of experimental flutter informationPreliminary investigation of short two-dimensional subsonic diffusersHeat of combustion of the product formed by the reaction of diborane and anunsaturated hydrocarbonRelation of currently estimated ANP performance to required ANP performanceEffect of tunnel configuration and testing technique on cascade performanceAnderson, Roger A1-Jul-5119930087867NACA-TN-2392Baker, Thomas F20-Aug-5319930087804NACA-RM-L53G06Cunningham, H J; Brown, Harvey HWoollett, Richard RAllen, Harrison, 53K25, LFPL-MZ-2Rothrock, Addison M; Cesaro, Richard SErwin, John R; Emery, James 7E13NACA-TN-2028Page 4 of 497 Pages
NACA-Limited to USG per 2013 NTRS ReviewTitleAuthorPublicationDateDocument IDReport/Patent NumberPerformance investigation of can-type combustor II : water injection at various stations incombustorAnalytical and experimental investigation of fully developed turbulent flow of air in asmooth tube with heat transfer with variable fluid propertiesStudy by the Prandtl-Glauert method of compressibility effects and critical Mach numberfor ellipsoids of various aspect ratios and thickness ratiosSummary of the lift, drag, and stability of 1/10-scale rocket-boosted models of theMcDonnell XF3H-1 airplane for a Mach number range of 0.6 to 1.4 as affected by theoperation of extensible rocket racks : TED No. NACA DE 351Zettle, Eugene V; Cook, William P30-Sep-4819930085473NACA-RM-E8F28Deissler, R G; Eian, C S1-Feb-5219930083475NACA-TN-2629Hess, Robert V; Gardner, Clifford S1-Jan-4919930082467NACA-TN-1792Crabill, Norman L; Mcfall, John C , Jr26-Jan-5419930088140NACA-RM-SL54A18Some effects of exposure to exhaust-gas streams on emittance and thermoelectric powerof bare-wire platinum rhodium - platinum thermocouplesA summary of diagonal tension Part II : experimental evidenceAnalysis of the turbojet for propulsion of supersonic bombersApproximate method for determining equilibrium operation of compressor component ofturbojet engineAerodynamic charact
Description of document: Listing of National Advisory Committee for Aeronautics (NACA) technical reports designated or identified in the National Aeronautics and Space Administration (NASA) Scientific and Technical Information (STI) database as restricted or nonpublic, 1944-1959 . Requested date: 17-March-2014 . Released date: 21-April-2014
E - Kit Tutorial - Optimising your ATDW Listing v1 Page 3 of 15 3 BENEFITS OF AN ATDW LISTING An ATDW listing has many benefits for tourism operators. These include: the ease of listing once, and the listing will appear on multiple websites the significant amount of exposure your listing will gain from appearing on a highly
ADD LISTING GUIDE Contents Resources Add Listing Rules Status Definitions How to Add A Listing into Flexmls . change is received by the Listing Broker. b) Within two (2) business days of acceptance of a purchase contract for a property entered in the MLS, the MLS listing must be reported as defined on the MLS's Status Change Form. .
ADD LISTING GUIDE Contents Resources Add Listing Rules Status Definitions How to Add A Listing into Flexmls . change is received by the Listing Broker. b) Within two (2) business days of acceptance of a purchase contract for a property entered in the MLS, the MLS listing must be reported as defined on the MLS's Status Change Form. .
MIT 401(k) Oversight Committee, 2014-2019. MIT Committee on Graduate Programs, 2017-2019. MIT International Advisory Committee . MITx Faculty Advisory Committee . MIT Sloan: International Initiatives Committee, Co-Chair of Space Committee, Chair of Load Committee, and Member of various standing committees, MIT Sloan School of Management, 2011-2015.
"Listing Agent" or "Lead Manager" a Capital Market Advisory Services Provider appointed by the Issuer to undertake the responsibility of finalizing the pre-listing requirements and fulfilling the ongoing obligations on behalf of the Issuer "Listing Rules" the provisions of BHB's listing rules as from time to
John Westbrook U.S. Army Field Artillery School, Ft. Sill Scott Keith Will Rogers World Airport First Round of Advisory Committees The Personal Travel Advisory Committee met on June 10, 2014 and the Freight Travel Advisory Committee met on June 11, 2014. The Tribal Transportation Advisory Committee met on July 17, 2014.
Sep 13, 2021 · 10:00 a.m. Programs and Projects Committee (PPC) 11:30 a.m. Planning, Policy and Legislation Committee (PPLC) 4:00 p.m. Alameda CTC Audit Committee October 28, 2021 : Advisory Committee Meetings : 1:30 p.m. Alameda County Technical Advisory Committee (ACTAC) September 9, 2021 O
Artificial Intelligence shaping the future of the built environment The ability of computers is transforming our lives at an increasing rate. The prospect of machines that can think, rather than just do, is something we are beginning to take for granted. The transformative power of artificial intelligence (AI) to change the infrastructure sector is only just beginning, but now is the time to .
