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  • Other Sources  (29)
  • Aircraft Design, Testing and Performance  (20)
  • Kartoffeln  (5)
  • ddc:554.3  (4)
  • Inorganic Chemistry
  • Organic Chemistry
  • 1980-1984
  • 1945-1949  (13)
  • 1935-1939  (9)
  • 1920-1924  (6)
  • 1915-1919  (1)
  • 1945  (13)
  • 1938  (9)
  • 1921  (6)
  • 1915  (1)
Collection
Source
Keywords
Publisher
Language
Years
  • 1980-1984
  • 1945-1949  (13)
  • 1935-1939  (9)
  • 1920-1924  (6)
  • 1915-1919  (1)
Year
  • 1
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    [Neue Nr. 5519] Hungen / Geologische Karte (1921)
    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:5519 | KART H 86:5519
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften der festen Erde), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; ddc:943.2 ; Geologische Karte ; Hungen
    Language: German
    Type: doc-type:carthographicMaterial
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    CITATION GEO-LEO
  • 2
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    [Neue Nr. 6118] Roßdorf / Geologische Karte (1938)
    Hessische Geologische Landesanstalt, Darmstadt
    In:  SUB Göttingen | KART B 104:6118 | KART H 86:6118
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Roßdorf ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 122
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    CITATION GEO-LEO
  • 3
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    [Neue Nr. 1860] Degow [Dygowo] / Geologische Karte (1921)
    Kraatz, Berlin
    In:  SUB Göttingen | KART B 140:1860 | KART H 140:Degow
    Details
    Publication Date: 2024-02-21
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: Nullmeridian Ferro E 033 20 - 033 30 / N 054 12 - 054 06.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 38
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    CITATION GEO-LEO
  • 4
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    [Neue Nr. 1760] Lassehne [Łasin Koszaliński] / Geologische Karte (1921)
    Kraatz, Berlin
    In:  SUB Göttingen | KART B 140:1760 | KART H 140:Lassehne
    Details
    Publication Date: 2024-02-21
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: Nullmeridian Ferro E 033 20 - 033 30 / N 054 18 - 054 12.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 38
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    CITATION GEO-LEO
  • 5
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    Witterungsverlauf und Ernteertrag in der Kurmark bei den Hauptgetreidearten und Kartoffeln. (1938)
    In:  Landwirtschaftl. Jahrbuch 86:823-924.
    Details
    Publication Date: 1938
    Description: Erarbeitung einer ausbaufähigen Methode für das Erfassen des Witterungsablaufes; Vergleichen einer Zwölfjahresreihe von Erträgen mit dem Witterungsablauf; bearbeitet wurden Winterroggen, Winterweizen, Wintergerste, Hafer, Sommergerste, Sommerweizen, Kartoffeln KATASTER-BESCHREIBUNG: Zusammenhang Witterung und Ertrag bei Getreide und Kartoffeln KATASTER-DETAIL: Delta Wasserversorgung (Frühjahr) - und Delta Wasserversorgung (Mai, Juni, Juli) +, dann Ertrag (Getreide) +; Delta T (frühe Entwicklungsstadien) -, dann Ertrag (Winterroggen, Hafer) +; Delta T (April) -, dann Ertrag (Hafer) +; Delta Nied (April, Mai) -, dann Ertrag (Winterweizen) +; delta T (Mai) -, dann Ertrag (Winterroggen) +; Delta T +, dann Ertrag (Kartoffel) +; Delta Nied (Juli, August) +, dann Ertrag (Kartoffel) +;
    Keywords: Brandenburg ; 1924-37 ; Kartoffeln ; Ertrag ; Getreide ; Witterung
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    BIBLIOGRAPHY INKA BB
  • 6
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    Niederschlags- und Erntemengen (1915)
    In:  Deut. Landwirtschaflt. Presse 42: 420-421
    Details
    Publication Date: 1915
    Description: Korrelation der Sommer- und Winterniederschläge (Oktober-März) mit den Erträgen von Sommer- und Winterweizen, Roggen, Hafer, Gerste, Zuckerrüben und Kartoffeln, Winterniederschläge sind entscheidend für die Erträge, aber ertragsrelevanter sind die Sommerniederschläge und hier nicht in der Häufigkei, sondern der Menge im Zusammenspiel mit Temperatur, Sonnenscheindauer etc. KATASTER-BESCHREIBUNG: Beziehung zwischen der Niederschlagshöhe und dem Ertrag verschiedener Kulturen, getrennt für Winter- und Sommerniederschläge als Grafiken KATASTER-DETAIL:
    Keywords: Schlesien und Sachsen-Anhalt ; 1888-1907 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Getreide ; Korrelationsmethode ; Niederschlag ; Roggen ; Weizen
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    BIBLIOGRAPHY INKA BB
  • 7
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    Hat das Wetter einen Einfluss auf die Form der Kartoffelknolle? (1921)
    In:  Die Kartoffel, S. 90
    Details
    Publication Date: 1921
    Description: Zusammenhang Niederschlag und Wachstum der Kartoffelknolle KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Niederschlag ; Trockenheit
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    BIBLIOGRAPHY INKA BB
  • 8
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    Der Einfluss der Witterung auf die Reifezeit usw. (1921)
    In:  Die Kartoffel, Seite 136
    Details
    Publication Date: 1921
    Description: Zusammenhang zwischen der Witterung und der Reifezeit der Kartoffelknolle KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Witterung
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    BIBLIOGRAPHY INKA BB
  • 9
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    Pflanzliche Schädlinge landwirtschaftlicher Kulturpflanzen. In: Pflanzenschutz und Landwirtschaft - Zwei Vorträge (Herausg.: Wehner, H.) (1921)
    In:  Schriften der oekonomischen Gesellschaft im Freistaat Sachsen 8; No.3; p.1-24
    Details
    Publication Date: 1921
    Description: Diskussion einiger wichtiger Pflanzenkrankheiten im Ackerbau, wie z.B. Brandkrankheiten verschiedener Kulturen und verschiedenen Kartoffelkrankheiten. Gestützt werden die Anmerkungen von regionalen Beispielen aus Deutschland. Teilweise wird Bezug zum Wetter hergestellt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1920-1921 ; Kartoffeln ; Getreide ; Pflanzenkrankheit ; Hackfrüchte
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    BIBLIOGRAPHY INKA BB
  • 10
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    Resistance Tests of Models of Three Flying-boat Hulls with a Length-beam Ratio of 10.5 (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-79 , NACA-ARR-L5G19
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 11
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    Wind-Tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semispan Ailerons and with Nonperforated, Balanced Double Split Flaps for Use as Aerodynamic Brakes (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flat-plate flaps with no wing cutouts and flaps having Clark Y sections with corresponding cutouts made in wing were tested for various flap deflections, chord-wise locations, and gaps between flaps and airfoil contour. The drag was slightly lower for wing with airfoil section flaps. Satisfactory aileron effectiveness was obtained with flap gap of 20% wing chord and flap-nose location of 80 percent wing chord behind leading edge. Airflow was smooth and buffeting negligible.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-56 , NACA-ARR-L5B17
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    NASA TECHNICAL REPORTS
  • 12
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    Effects of Wing and Nacelle Modifications on Drag and Wake Characteristics of a Bomber-Type Airplane Model (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of a model of a large four-engine bomber was conducted in the Langley 19-f'oot pressure tunnel to determine the effects of several wing and nacelle modifications on drag characteristics and air flow characteristics at the tail. Leading-edge gloves, trailing-edge extensions, and modified nacelle afterbodies were tested individual ly and in combination. The effects of the various modifications were determined by force tests, tuft observations, and turbulence s1ITveys in the region of the tail. Tests were made with fixed and natural transition on the wing and with propellers operating and propellers off. Most of the tests were con- ducted at a Reynolds number of approximately 2.6 x 106. The results indicated that application of certain of the modifications provided worth-while improvements in the characteristics or the model. The flow over the wing and flaps was improved, the drag was reduced, and the turbulence in the region of the tail was reduced. Trailing-edge extensions were the most effective individual modification in improving the flow over the wing with wing flaps neutral, cowl and intercooler flaps clos ed. Modified nacelle afterbodies were the most effectiv8 individual edification in reducing drag with either fixed or natural transition on the wing; however, trailin6-edge extensions were slightly more effective with fixed transition. Combinations of either leading or trailing-edge extensions and modified afterbodies were more effective than either modification alone. With cowl and intercooler flaps open, trailing-edge extensions with modified afterbodies provided substantial improvement in flow and drag characteristics. With wing flaps deflected, enclosing the flap behind the inboard nacelle within an extended afterbody or cutting the flaps at the nacelle appeared. to be the most promising methods of improving the f low over the flaps and the tail. Although the results of hot-wire-anenometer surveys were not conclusive in regard to buffeting characteristics, the modifications did educe the turbulence at the tail with wing flaps both neutral and deflected. The modifications, as a rule, were favorable to maximum lift. Appreciable reductions in longitudinal stability of the model were caused by addition of leading -edge gloves and tr ailing -edge extensions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-114 , NACA-ARR-L5J05
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-188 , NACA-ACR-L5G18
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    NASA TECHNICAL REPORTS
  • 14
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    Blade Motion and Bouncing Tests of KD-1 Autogiro (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: There are forwarded herewith the results of blade motion and bouncing tests on the Kellett KD-1 three-bladed autogiro. Motion picture records and two-component accelerometer records were taken in flight during glides at air speeds from 30 miles per hour to 100 miles per hour indicator readings. Calibration curves of correct indicated air speed and rotor speed as functions of air speed meter reading were established with a trailing pitot-static head and a rotoscope, at 2,000 ft. altitude and an air density of 0.00231 slug/ cu. ft., all tests being made at approximately that density.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-X-1935
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    NASA TECHNICAL REPORTS
  • 15
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    New Method of Determining the Polar Curve of an Airplane in Flight (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A fundamental defect of existing methods for the determination of the polar of an airplane in flight is the impossibility of obtaining the thrust or the resistance of the propeller for any type airplane with any type engine. The new method is based on the premise that for zero propeller thrust the mean angle of attack of the blade is approximately the same for all propellers if this angle is reckoned from the aerodynamic chord of the profile section. This angle was determined from flight tests. Knowing the mean angle of the blade setting the angle of attack of the propeller blade at zero thrust can be found and the propeller speed in gliding obtained. The experimental check of the new method carried out on several airplanes gave positive results. The basic assumptions for the construction of the polars and the method of analyzing the flight data are given.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1076 , Report of the Central Aero-Hydrodynamical Inst.; Rept-418
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    NASA TECHNICAL REPORTS
  • 16
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    An Experimental Investigation of NACA Submerged-Duct Entrances (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The results of an investigation of submerged-duct entrances are presented. It is shown that this type of entrance possesses the following characteristics: 1) very high-critical-compressibility speeds throughout the range of high-speed inlet velocity ratios; 2) very low pressure losses for the air entering the duct at all inlet-velocity ratios; and, 3) low external drag. These characteristics are obtained by the proper shaping of the contour of the upstream approach to the submerged inlets and by proper alignment of the duct lip. Design data are presented and the application of these data to a specific high-speed fighter-airplane design is discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-A5E23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Correlation of the characteristics of single-cylinder and flight engines in tests of high-performance fuels in an air-cooled engine II : knock-limited charge-air flow and cylinder temperatures (1945)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: An investigation was conducted to correlate the knock limited performance of flight and single-cylinder engines under a variety of operating conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-E-272 , NACA-MR-E5J12
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    NASA TECHNICAL REPORTS
  • 18
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    Preliminary Fatigue Studies on Aluminum Alloy Aircraft Girders (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Preliminary information on the complex subject of the fatigue strength of fabricated structural members for aircraft is presented in the test results obtained on several different types of airship girders subjected to axial tension and compression in a resonance fatigue machine. A description of this machine as well as numerous photographs of the fatigue failures are given. There is also presented an extended bibliography on the subject of fatigue strength.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-637
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    NASA TECHNICAL REPORTS
  • 19
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    Calculation of Centrally Loaded Thin-Walled Columns Above the Buckling Limit (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: When thin-walled columns formed from flanged sheet, such as used in airplane construction, are subjected to axial load, their behavior at failure varies according to the slenderness ratio. On long columns the axis deflects laterally while the cross section form is maintained; buckling results. The respective breaking load in the elastic range is computed by Euler's formula and for the plastic range by the Engesser- Karman formula. Its magnitude is essentially dependent upon the length. On intermediate length columns, especially where open sections are concerned, the cross section is distorted while the cross section form is preserved; twisting failure results. The buckling load in twisting is calculated according to Wagner and Kappus. On short columns the straight walls of low-bending resistance that form the column are deflected at the same time that the cross section form changes - buckling occurs without immediate failure. Then the buckling load of the total section computable from the buckling loads of the section walls is not the ultimate load; quite often, especially on thin-walled sections, it lies considerably higher and is secured by tests. Both loads, the buckling and the ultimate load are only in a small measure dependent upon length. The present report is an attempt to theoretically investigate the behavior of such short, thin-walled columns above the buckling load with the conventional calculating methods.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1077 , Luftfahrtforschung; 19; 7; 240-247
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    NASA TECHNICAL REPORTS
  • 20
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    An Experimental Investigation of NACA Submerged-Duct Entrances (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The results of a preliminary investigation of submerged duct entrances are presented. It is shown that an entrance of this type possess desirable critical speed and pressure recovery characteristics when used on a fuselage or nacelle in a region of low incremental velocity and thin boundary layer. The data obtained indicate that submerged entrances are most suitable for use with internal-flow systems which diffuse the air only a small amount: for example, those used with jet motors which have axial-flow compressors. Where complete diffusion of the air is required, fuselage-nose or wing leading edge inlets may prove to be superior. The results of the investigation have been prepared in such a form as to permit their use by a designer and the application of these data to a specific design is discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-ACR-5I20
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    NASA TECHNICAL REPORTS
  • 21
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    Preliminary Full-Scale Wind-Tunnel Investigation of Wing Ducts for Radiators, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wing ducts for liquid-cooled engine radiators have been investigated in the N.A.C.A. full-scale wind tunnel on a large model airplane. Th e tests were made to determine the relative merits of several types of duct and radiator installations for an airplane of a particular des ign. In the test program the principal duct dimensions were system atically varied, and the results are therefore somewhat applicable to the general problems of wing duct design, although they should be co nsidered as preliminary and only indicative of the inherent possibil ities.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-88
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    NASA TECHNICAL REPORTS
  • 22
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    Wind-Tunnel Investigation of Air Inlet and Outlet Openings for Aircraft, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was made in the NACA 5-foot vertical wind tunnel of a large variety of duct inlets and outlets to obtain information relative to their design for the cooling or the ventilation systems on aircraft. Most of the tests were of openings in a flat plate but, in order to determine the best locations and the effects of interference, a few tests were made of openings in an airfoil. The best inlet location for a system not including a blower was found to be at the forward stagnation point; for one including a blower, the best location was found to be in the region of lowest total head, probably in the boundary layer near the trailing edge. Design recommendations are given, and it is shown that correct design demands a knowledge of the external flow and of the internal requirements in addition to that obtained from the results of the wind tunnel tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-95
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    NASA TECHNICAL REPORTS
  • 23
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    Full-Scale Wind-Tunnel Investigation of Wing Cooling Ducts, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The systematic investigation of wing cooling ducts at the NACA laboratory has been continued with tests in the full-scale wind tunnel on ducts of finite span. These results extend the previous investigation on section characteristics of ducts to higher Reynolds numbers and indicate the losses due to the duct ends. The data include comparisons between ducts completely within the ring and the conventional underslung ducts. Methods of flow regulation were studied and data were obtained for a wide range of internal duct resistance. The results show satisfactory correlation between the finite span and the previously measured section characteristics obtained with full-span ducts. The effects of the various design parameters on the duct characteristics are discussed. The cooling power required for the internal duct installation is shown to be only a small percentage of the engine power.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-94
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  • 24
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    Investigation in the 7-By-10 Foot Wind Tunnel of Ducts for Cooling Radiators Within an Airplane Wing, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was made in the NACA 7- by 10-foot wind tunnel of a large-chord wing model with a duct to house a simulated radiator suitable for a liquid-cooled engine. The duct was expanded to reduce the radiator losses, and the installation of the duct and radiator was made entirely within the wing to reduce form and interference drag. The tests were made using a two-dimensional flow set-up with a full-span duct and radiator. Section aerodynamic characteristics of the basic airfoil are given and also curves showing the characteristics of the various duct-radiator combinations. An expression for efficiency, the primary criterion of merit of any duct, and the effect of the several design parameters of the duct-radiator arrangement are discussed. The problem of throttling is considered and a discussion of the power required for cooling is included. It was found that radiators could be mounted in the wing and efficiently pass enough air for cooling with duct outlets located at any point from 0.25c to 0.70c from the wing leading edge on the upper surface. The duct-inlet position was found to be critical and, for maximum efficiency, had to be at the stagnation point of the airfoil and to change with flight attitude. The flow could be efficiently throttled only by a simultaneous variation of duct inlet and outlet sizes and of inlet position. It was desirable to round both inlet and outlet lips. With certain arrangements of duct, the power required for cooling at high speed was a very low percentage of the engine power.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-93
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    NASA TECHNICAL REPORTS
  • 25
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    The Torsional and Bending Deflection of Full-Scale Duralumin Propeller Blades under Normal Operating Conditions, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The torsional deflection of the blades of three full-scale duralumin propellers operating under various loading conditions was measured by a light-beam method. Angular bending deflections were also obtained as an incidental part of the study. The deflection measurements showed that the usual present-day type of propeller blades twisted but a negligible amount under ordinary flight conditions. A maximum deflection of about 1/10th of a degree was found at V/nD of 0.3 and a smaller deflection at higher values of V/nD for the station at 0.70 radius. These deflections are much smaller than would be expected from earlier tests, but the light-beam method is considered to be much more accurate than the direct-reading transit method used in the previous tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-84
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    NASA TECHNICAL REPORTS
  • 26
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    Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail Incorporating a De-Icing Air Duct (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage, stub horizontal tail, and a de-icing air duct was tested in the Langley stability tunnel. The investigation consisted of a study of the effects of the duct, with and without air flow, on the aerodynamic characteristics of the model. The model tested was a revision of a model previously tested in the Langley stability tunnel. The revised model differed from the original model in that it incorporated a de-icing air duct, included a dorsal fin, and had a larger stub fuselage. A comparison of data obtained form tests of the original and revised models was made. The results of the investigation indicated that the air duct had very little effect on the aerodynamic characteristics of the model. A small change occurred in the variation of rudder hinge-moment coefficient with angle of attack but it is believed that this change can be corrected by a properly applied spring tab.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-L5G18a
    Format: application/pdf
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  • 27
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    An Experimental Investigation of Several Low-Drag Wing-Nacelle Combinations with Internal Air Flow (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The results of an experimental investigation of several low-drag wing-nacelle combinations, incorporating internal air-flow systems, are presented. The external-drag increments due to these nacelles are between one-half and two-thirds of those of conventional nacelle forms. This improvement is accomplished with only minor effects on the lift and moment characteristics of the wing. The procedure employed to determine the external shape of such low-drag nacelles is considered in detail. The design of an efficient internal-flow system with or without a blower or throttle, presents no serious problems. The energy losses in the expansion before the engine and the contraction thereafter can be kept small. It is believed that these nacelles have a wide application in housing engine pusher-propeller units and, with some alteration, jet-propulsion devices. It is probable that the low external drags may not be realized if such nacelles are used with a tractor propeller because of the high level of turbulence in the propeller slipstream.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA ACR-5A15
    Format: application/pdf
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  • 28
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    N.A.C.A. Stall-Warning Device (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: With some airplanes the approach to the stall is accompanied by changes in the behavior, such as tail buffeting or changes in the control characteristics of the airplane so that the pilot obtains a warning of the impending stall. Vith other airplanes it is possible to approach the stall without any perceptible warning other than the reading of the air-speed meter, in which case the danger of inadvertent stalling is considerably greater. Although it is not within the scope of this paper to discuss stalling characteristics, it is desired to point out that in general the danger of inadvertent stalling is greatest with those airplanes that behave worse when the stalling occurs; that is, with airplanes in which the stall starts at the wing tips. A warning of the impending stall is desirable in any case, but is particularly desirable with airplanes of the latter type.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-80
    Format: application/pdf
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  • 29
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    Wind-Tunnel Tests of a Portion of a PV-2 Helicopter Rotor Blade (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the blade. Because the tunnel wall acts as a plane of sy~try, the measured aerodynamic characteristics correspond to those of an airfoil having various angles of sweepforward and sweepback. Tests were made with the vents on the lower surface open and also with the vents sealed and the internal pressure held at -20 inches of water producing an internal pressure coefficient of -1.059. The change in contour resulting from the range of internal pressures used had very little effect on the aerodynamic characteristics of the blade. The test methods were considered to simulate inadequately the flow conditions over the rotor blade because the effects of cross flow were limited to conditions corresponding to sweep of the blade. The results indicated that this type of cross flow had only minor effects on the aerodynamic characteristics of the blade. It is believed, therefore, that future tests to determine the effects on the aerodynamic characteristics of cross flow should utilize complete rotors.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-L5C29b
    Format: application/pdf
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