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  • Other Sources  (31)
  • Aerodynamics  (16)
  • Seismology  (14)
  • EOS  (3)
  • Industrial Chemistry
  • Inorganic Chemistry
  • Mice
  • 2010-2014
  • 1950-1954  (25)
  • 1940-1944  (6)
  • 1951  (25)
  • 1940  (6)
  • 1
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    Progress report, Seismological Laboratory, California Institute of Technology, 1950 (1951)
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 32, no. 3-4, pp. 749-753, pp. 1246
    Details
    Publication Date: 1951
    Keywords: Seismology ; Project report/description ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Travel times from blasts in Southern California (1951)
    In:  Bull. Seism. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 41, no. 6, pp. 5-12, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: Travel time ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Earthquakes (1951)
    In:  Istanbul Teknik Üniversitesi Bülteni, Milano, California Institute of Technology Pasadena, vol. 4, no. 6, pp. 66-70, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: Seismology ; Seismicity ; Istanbul
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Larger shocks of 1950 (1951)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1950, no. 6, pp. 102-103, pp. L24306, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1951
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Surface waves recorded by a Benioff vectorial seismograph (1951)
    In:  Bull. Geol. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 62, no. 6, pp. 1527, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: Surface waves ; Seismology ; Seismometer
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    PKKP, P'P', and the earth's core (1951)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 32, no. 6, pp. 373-390, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: Waves ; earth Core ; Seismology ; P-waves ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Revised travel times in Southern California (1951)
    In:  Bull. Seism. Soc. Am., Milano, California Institute of Technology Pasadena, vol. 41, no. 6, pp. 143-164, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: Travel time ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Colloquium on plastic flow and deformation within the earth (Hershey, Pennsylvania, September 12-14, 1950) (1951)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 32, no. 6, pp. 497-543, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1951
    Keywords: Elasticity ; Rock mechanics ; Rheology ; Fluids ; Earth model, also for more shallow analyses ! ; EOS ; BIBTEX? ; ENDNOTE?
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Earthquakes and rock creep, part 1 (1951)
    In:  Bull. Seism. Soc. Am., Beijing, Pergamon, vol. 41, no. 3-4, pp. 184-190, pp. 1246
    Details
    Publication Date: 1951
    Keywords: Fracture ; Rock mechanics ; Rheology ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Evidence from deep-focus earthquakes (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. XI:, pp. 305-313, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: Seismology ; Hypocentral depth
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    The elastic constants in the interior of the earth (1951)
    Dover Publ.
    In:  Professional Paper, Internal constitution of the earth - Physic of the earth, Dover, 439 pp., Dover Publ., vol. 7, no. XIV:, pp. 364-381, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1951
    Keywords: Elasticity ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Observations and theory of microseisms (1951)
    Am. Meteor. Soc.
    In:  Professional Paper, Compendium of Meteorology, Dover, 439 pp., Am. Meteor. Soc., vol. 7, no. XVI:, pp. 1303-1311, (ISBN: 3-540-23712-7)
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    Publication Date: 1951
    Keywords: Micro seismicity ; Seismology ; NOISE
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    Earthquakes in North America (1951)
    Smithsonian Institute
    In:  Ann. Rep. 1950, Toronto, Smithsonian Institute, vol. 10, no. GL-TR-89-0230, pp. 303-316, (ISBN 3-933346-037)
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    Publication Date: 1951
    Keywords: Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    Preliminary Investigation of a New Type of Supersonic Inlet (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than the drag coefficient for the type of inlet with supersonic compression entirely inside, but the pressure recovery is larger for all flight conditions. The differences in drag can be eliminated for the design Mach number. Experimental results confirm the results of the theoretical analysis and show that pressure recoveries of 95 percent for Mach numbers of 1.33 and 1.52, 92 percent for a Mach number of 1.72, and 86 percent for a Mach number of 2.10 are possible, with the configurations considered. If the mass flow decreases, the total drag coefficient increases gradually and the pressure recovery does not change appreciably. The results of this work were first presented in a classified document issued in 1946.
    Keywords: Aerodynamics
    Type: NACA-TN-2286
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  • 15
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    Systematic Two-Dimensional Cascade Tests of NACA 65-Series Compressor Blades at Low Speeds (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The performance of NACA 65-series compressor blade section in cascade has been investigated systematically in a low-speed cascade tunnel. Porous test-section side walls and for high-pressure-rise conditions, porous flexible end walls were employed to establish conditions closely simulating two-dimensional flow. Blade sections of design lift coefficients from 0 to 2.7 were tested over the usable angle-of-attack range for various combinations of inlet-flow angle. A sufficient number of combinations were tested to permit interpolation and extrapolation of the data to all conditions within the usual range of application. The results of this investigation indicate a continuous variation of blade-section performance as the major cascade parameters, blade camber, inlet angle, and solidity were varied over the test range. Summary curves of the results have been prepared to enable compressor designers to select the proper blade camber and angle of attack when the compressor velocity diagram and desired solidity have been determined.
    Keywords: Aerodynamics
    Type: NACA-TR-1368 , NACA-RM-L51G31
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  • 16
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    Wind-tunnel investigation of the descent characteristics of bodies of revolution simulating anti-personnel bombs (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted in the Langley 20-foot free spinning tunnel to study the relative behavior in descent of a number of homogeneous balsa bodies of revolution simulating anti-personnel bombs with a small cylindrical exploding device suspended approximately 10 feet below the bomb. The bodies of revolution included hemispherical, near-hemispherical, and near-paraboloid shapes. The ordinates of one near-paraboloid shape were specified by the Office of the Chief of Ordnance, U. S. Army. The behavior of the various bodies without the cylinder was also investigated. The results of the investigation indicated that several of the bodies descended vertically with their longitudinal axis, suspension line, and small cylinder in a vertical attitude,. However, the body, the ordinates of which had been specified by the Office of the Chief of Ordnance, U. S. Army, oscillated considerably from a vertical attitude while descending and therefore appeared unsuitable for its intended use. The behavior of this body became satisfactory when its center of gravity was moved well forward from its original position. In general, the results indicated that the descent characteristics of the bodies of revolution become more favorable as their shapes approached that of a hemisphere.
    Keywords: Aerodynamics
    Type: NACA-RM-SL51L13
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  • 17
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    The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The subject of this paper is the drag of the nose section of bodies of revolution at zero angle of attack. The magnitude of the nose drag in relation to the total drag is very distinctly a function of the body design and the Mach number. It can range from a very small fraction of the total drag of the order of 10 percent to a very large fraction as high as 80 percent. The natural objective of nose design is to minimize the drag, but this objective is not always the primary one. Sometimes other factors overshadow the desire for minimum drag. The most conspicuous example of this is the proposal of guidance engineers that large-diameter spheres and other very blunt shapes be used at the nose tip. This paper will attempt to discuss both phases of the problem, noses for minimum drag and noses with very blunt tips. The state of the theory will also be reviewed and recent theoretical developments described, since the theory still remains a very valuable tool for assaying the effects of compromises in design and departure from shapes for which experimental data are available.
    Keywords: Aerodynamics
    Type: Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers; 1-12; NACA-RM-A51J25|NACA Conference on Aerodynamic Design Problems of Supersonic Guided Missiles; Oct 02, 1951 - Oct 03, 1951; Moffett Field, CA; United States
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  • 18
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    An Investigation of the Aerodynamic Characteristics in Pitch of an XB-52 Airplane Model in a High-Speed Wind Tunnel (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A wind-tunnel investigation of a 0.049-scale model of the Boeing XB-52 airplane was made at Mach numbers from 0.30 to 0.925 and at corresponding Reynolds numbers from about 2.3 x 10(exp 6) to 4.3 x 10(exp 6). The results of the investigation indicate satisfactory static longitudinal stability throughout the test Mach-number range and some loss in tail effectiveness beginning at about 0.80 Mach number. A comparison of the results of these tests with those of the same model in the Boeing Airplane Company's wind tunnel showed close agreement of lift- and drag-divergence Mach numbers. Slight differences were observed in tail effectiveness and the position of the stick-fixed neutral point.
    Keywords: Aerodynamics
    Type: NACA-RM-SA51C16
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  • 19
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    Supplementary Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane in the Swept-Wing Configuration with Slats Extended (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel of a 1/30 -scale model of the Grumman XFlOF-1 airplane to determine what effect full-span slats would have on the spin-recovery characteristics of the swept-wing version of the XFlOF-1 airplane, which had previously been indicated as possessing undesirable spin-recovery characteristics without slats. The effects of extended nose-wheel doors and of fairing the air-duct inlets were also determined. The results indicated that, with slats fully extended, satisfactory recovery could be obtained by rudder reversal provided it was accompanied by movement of the trimmer ailerons to full with the spin (only up-going spoiler operative), Extension of the nose-wheel doors or fairing of the air-duct inlets did not improve the recovery characteristics.
    Keywords: Aerodynamics
    Type: NACA-RM-SL51G19
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  • 20
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    Damping in a Roll of a Missile Configuration with a Modified Triangular Wing and a Cruciform Tail at a Mach Number of 1.52 (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The damping-in-Toll stability derivatives of a missile configuration and its components were determined both experimentally and theoretically. The tests were conducted at a Mach number of 1.52 and at a Reynolds number, based on the mean aerodynamic chord of the wing, of 0.82 x 10(exp 6). The experimental damping derivative of the wing-body combination was 67 percent of the theoretical value. The difference is believed to have resulted mainly from the fact that the theory is not strictly applicable when the Mach number normal to the leading edge is almost unity, which was the case in the present investigation. For the tail-body combination the damping derivative was 86 percent of the theoretical value. In this case, the difference is believed to have been caused partially by mutual interference between the tail surfaces and partially by the low Reynolds number of the flow over the tail. It was found that the damping of the complete configuration was not equal to the sum of the damping derivatives of the components because of the effect of the wing downwash on the damping of the tail.
    Keywords: Aerodynamics
    Type: NACA-RM-A51A03
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  • 21
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    Lift, Drag, and Pitching Moment of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds: Triangular Wing of Aspect Ratio 2 with NACA 0005-63 Thickness Distribution, Cambered and Twisted for a Trapezoidal Span Load Distribution (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A wing-body combination having a plane triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution in streamwise planes, and twisted and cambered for a trapezoidal span load distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.60 to 0.90 and 1.30 to 1.70 at a Reynolds number of 3.0 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers.
    Keywords: Aerodynamics
    Type: NACA-RM-A50K27a
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  • 22
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    Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206 (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a flying-boat hull of a length-beam ratio of 15 in the presence of a wing. The investigation was an extension of previous tests made on hulls of length-beam ratios of 6, 9, and 12; these hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Comparison with the previous investigation at lower length-beam ratios indicated a reduction in minimum drag coefficients of 0.0006 (10 peroent)with fixed transition when the length-beam ratio was extended from 12 to 15. As with the hulls of lower length-beam ratio, the drag reduction with a length-beam ratio of 15 occurred throughout the range of angle of attack tested and the angle of attack for minimum drag was in the range from 2deg to 3deg. Increasing the length-beam ratio from 12 to 15 reduced the hull longitudinal instability by an mount corresponding to an aerodynamic-center shift of about 1/2 percent of the mean aerodynamic chord of the hypothetical flying boat. At an angle of attack of 2deg, the value of the variation of yawing-moment coefficient with angle of yaw for a length-beam ratio of 15 was 0.00144, which was 0.00007 larger than the value for a length-beam ratio of 12.
    Keywords: Aerodynamics
    Type: NACA-RM-L6J24
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  • 23
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    Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.87 to 1.39 of 1/10-Scale Models of the Northrop MX-775A Missile (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A flight investigation was made at high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a 1/10-scale model of the Northrop MX-775A missile and a scale model of the missile fuselage. The model of the complete configuration has a 45deg swept wing of aspect ratio 5.5 and a 33deg swept vertical fin. The body model was stabilized by three 45deg swept fins. The-drag-rise Mach number for the model of the complete configuration was approximately 0.96. The drag coefficient based on total wing area was 0.0330 at Mach number 1.39. The drag coefficient of the body model less fin drag was approximately 55 percent that of the complete model at the same Mach number. Addition of the wing to the fuselage apparently resulted in a favorable drag interference near Mach number 1.0.
    Keywords: Aerodynamics
    Type: NACA-RM-SL51K07
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  • 24
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    Base Pressure on Wings and Bodies with Turbulent Boundary Layers (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: At present there is no satisfactory theory for calculating the pressure which acts at the blunt base of an object traveling at supersonic velocity. In fact, the essential mechanism determining the base pressure is only imperfectly understood. As a result, the existing knowledge of base pressure is based almost entirely on experiments. The main object of this paper is to summarize the principal results of the many wind tunnel and free flight measurements of base pressure on both bodies of revolution and blunt trailing edge airfoils. A relatively simple method of estimating base pressure is presented, and an indication is given as to how the characteristics of base pressure play an essential role in determining the shape of an aerodynamically efficient object for supersonic flight.
    Keywords: Aerodynamics
    Type: Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers; 13-30; NACA-RM-A51J25|NACA Conference on Aerodynamic Design Problems of Supersonic Guided Missiles; Oct 02, 1951 - Oct 03, 1951; Moffett Field, CA; United States
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  • 25
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    Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The three papers collected here are: 'The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack.', 'Base Pressure on Wings and Bodies with Turbulent Boundary Layers', and 'Flow over Inclined Bodies'. The subject of the first paper is the drag of the nose section of bodies of revolution at zero angle of attack. The main object of the second paper is to summarize the prinicpal results of the many wind tunnel and free flight measurements of base pressure on both bodies of revolution and blunt trailing edge airfoils.
    Keywords: Aerodynamics
    Type: NACA-RM-A51J25
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  • 26
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    Seismological Tables (1940)
    British Association for the Advancement of Science, Gray Milne Trust
    In:  London, 50 pp., 4th print., 1970, British Association for the Advancement of Science, Gray Milne Trust, vol. 46, no. XVI:, pp. 1-14, (ISBN: 0-387-30752-4)
    Details
    Publication Date: 1940
    Keywords: Earth model, also for more shallow analyses ! ; Travel time ; Seismology ; Handbook of geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 27
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    Deep focus earthquakes in America (1940)
    University of California Press
    In:  Pacific Science Association, 6th Congress Proceedings, vol. 1, Toronto, University of California Press, vol. 10, no. GL-TR-89-0230, pp. 149-150, (ISBN 3-933346-037)
    Details
    Publication Date: 1940
    Keywords: Seismology ; Seismicity ; Hypocentral depth
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  • 28
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    Wind-tunnel Tests of the NACA 45-125 Airfoil: A Thick Airfoil for High-Speed Airplanes (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Investigations of the pressure distribution, the profile drag, and the location of transition for a 30-inch-chord 25-percent-thick N.A,C.A. 45-125 airfoil were made in the N.A.C.A 8-foot high-speed wind tunnel for the purpose of aiding in the development of a thick wing for high-speed airplanes. The tests were made at a lift coefficient of 0.1 for Reynolds Numbers from 1,750,000 to 8,690,000, corresponding to speeds from 80 to 440 miles per hour at 59 F. The effect on the profile drag of fixing the transition point was also investigated. The effect of compressibility on the rate of increase of pressure coefficients was found to be greater than that predicted by a simplified theoretical expression for thin wings. The results indicated that, for a lift coefficient of 0.1, the critical speed of the N.A.C,A. 45-125 airfoil was about 460 miles per hour at 59 F,. The value of the profile-drag coefficient at a Reynolds Number of 4,500,000 was 0.0058, or about half as large as the value for the N.A,C,A. 0025 airfoil. The increase in the profile-drag coefficient for a given movement of the transition point was about three times as large as the corresponding increase for the N.A.C,A. 0012 airfoil. Transition determinations indicated that, for Reynolds Numbers up to ?,000,000, laminar boundary 1ayers were maintained over approximately 40 percent of the upper and the lower surfaces of the airfoil.
    Keywords: Aerodynamics
    Type: NACA-SR-138
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  • 29
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    Wind-Tunnel Investigation of the Lift Characteristics of an NACA 27-212 Airfoil Equipped with Two Types of Flap, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 27-212 airfoil with a 20% chord split flap and with two arrangements of a 25.66% chord slotted flap to determine the section lift characteristics as affected by flap deflection for the split flap and as affected by flap deflection, flap position, and slot shape for the slotted flap. For the two arrangements of the slotted flap, the flap positions for maximum section lift are given. Comparable data on the NACA 23012 airfoil equipped with similar flaps are also given. On the basis of maximum section lift coefficient, the slotted flap with an easy slot entry was slightly better than either the split flap or the slotted flap with a sharp slot entry. With both types of flap the decrease in the angle of attack, for maximum section lift coefficient, with flap deflection is large for the NACA 27-212 airfoil as compared with the NACA 23012 airfoil. Also with both flaps, the maximum section lift coefficient obtained with flaps is much lower for the NACA 27-212 airfoil than for the NACA 23012 airfoil.
    Keywords: Aerodynamics
    Type: NACA-SR-159
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  • 30
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    Full-Scale Tests of Several Propellers Equipped with Spinners, Cuffs, Airfoil and Round Shanks, and NACA 16-Series Sections, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of several propeller, cuff, and spinner combinations were conducted in the 20 foot propeller-research tunnel. Three propellers, which ranged in diameter from 8.4 to 11.25 feet, were tested at the front end of a streamline body incorporating spinners of two diameters. The tests covered a blade angle range from 20 deg to 65 deg. The effect of spinner diameter and propeller cuffs on the characteristics of one propeller was determined. Test were also conducted using a propeller which incorporated aerodynamically good shank sections and using one which incorporated the NACA 16 series sections for the outer 20 percent of the blades. Compressibility effects were not measured, owing to the low testing speeds. The results indicated that a conventional propeller was slightly more efficient when tested in conjunction with a 28 inch diameter spinner than with a 23 inch spinner, and that cuffs increased the efficiency as well as the power absorption characteristics. A propeller having good aerodynamic shanks was found to be definitely superior from the efficiency standpoint to a conventional round-shank propeller with or without cuffs; this propeller would probably be considered structurally impracticable, however. The propeller incorporating the NACA 16 series sections at the tims were found to have a slightly higher efficiency than a conventional propeller; the take-off characteristics appeared to be equally good. The effects noted above probably would be accentuated at helical speeds at which compressibility effects would enter.
    Keywords: Aerodynamics
    Type: NACA-SR-168
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  • 31
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    Boundary-Layer Transition on the N.A.C.A. 0012 and 23012 Airfoils in the 8-Foot High-Speed Wind Tunnel, Special Report (1940)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Determinations of boundary-layer transition on the NACA 0012 and 2301 airfoils were made in the 8-foot high-speed wind tunnel over a range of Reynolds Numbers from 1,600,000 to 16,800,000. The results are of particular significance as compared with flight tests and tests in wind tunnels of appreciable turbulence because of the extremely low turbulence in the high-speed tunnel. A comparison of the results obtained on NACA 0012 airfoils of 2-foot and 5-foot chord at the same Reynolds Number permitted an evaluation of the effect of compressibility on transition. The local skin friction along the surface of the NACA 0012 airfoil was measured at a Reynolds Number of 10,000,000. For all the lift coefficient at which tests were made, transition occurred in the region of estimated laminar separation at the low Reynolds Numbers and approach the point of minimum static pressure as a forward limit at the high Reynolds Numbers. The effect of compressibility on transition was slight. None of the usual parameters describing the local conditions in the boundary layer near the transition point served as an index for locating the transition point. As a consequence of the lower turbulence in the 8-foot high-speed tunnel, the transition points occurred consistently farther back along the chord than those measured in the NACA full-scale tunnel. An empirical relation for estimating the location of the transition point for conventional airfoils on the basis of static-pressure distribution and Reynolds Number is presented.
    Keywords: Aerodynamics
    Type: NACA-SR-137
    Format: application/pdf
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