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  • 1
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    Tests of Propeller-speed Cooling Blowers (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-455
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental Verification of the Theory of Oscillating Airfoils (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements have been made of the lift on an airfoil in pitching oscillation with a continuous-recording, instantaneous-force balance. The experimental values for the phase difference between the angle of attack and the lift are shown to be in close agreement with theory.
    Type: NACA-TR-673
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Ground-Handling Forces on a 1/40-scale Model of the U. S. Airship "Akron." (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of full-scale wind tunnel tests conducted to determine the ground-handling forces on a 1/40-scale model of the U. S. Airship "Akron." Ground-handling conditions were simulated by establishing a velocity gradient above a special ground board in the tunnel comparable with that encountered over a landing field. The tests were conducted at Reynolds numbers ranging from 5,000,000 to 19,000,000 at each of six angles of yaw between 0 degree and 180 degrees and at four heights of the model above the ground board. The ground-handling forces vary greatly with the angle of yaw and reach large values at appreciable angles of yaw. Small changes in height, pitch, or roll did not critically affect the forces on the model. In the range of Reynolds numbers tested, no significant variation of the forces with the scale was disclosed.
    Type: NACA-TR-566
    Format: application/pdf
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  • 4
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    Experimental Investigation of Wind-Tunnel Interference on the Downwash Behind an Airfoil (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The interference of the wind-tunnel boundaries on the downwash behind an airfoil has been experimentally investigated and the results have been compared with the available theoretical results for open-throat wind tunnels. As in previous studies, the simplified theoretical treatment that assumes the test section to be an infinite free jet has been shown to be satisfactory at the lifting line. The experimental results, however, show that this assumption may lead to erroneous conclusions regarding the corrections to be applied to the downwash in the region behind the airfoil where the tail surfaces are normally located. The results of a theory based on the more accurate concept of the open-jet wind tunnel as a finite length of free jet provided with a closed exit passage are in good qualitative agreement with the experimental results.
    Type: NACA-TR-609
    Format: application/pdf
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  • 5
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    Liquid hydrogen as a jet fuel for high-altitude aircraft (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-E55C28a
    Format: application/pdf
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  • 6
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    Full Scale Span Load Distribution on a Tapered Wing with Split Flaps of Various Spans (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pressure-distribution tests were conducted in the full-scale wind tunnel on a 2:1 tapered U.S.A. 45 airfoil equipped with 20 percent chord split trailing-edge flaps of various spans. A special installation was employed in the tests utilizing a half-span airfoil mounted vertically above a reflection plane. The airfoil has a constant chord center section and rounded tips and is tapered in thickness from 18 percent c at the root to 9 percent c at the tip. The aerodynamic characteristics, given by the usual dimension less coefficients, are presented graphically as functions of flap span and angle of attack as well as by semispan load diagrams. The results indicate, in general, that only a relatively small increase in the normal-force coefficient is to be expected by extending the flap span of an airfoil-flap combination, similar to the one tested, beyond 70 percent of the wing span.
    Type: NACA-TN-591
    Format: application/pdf
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  • 7
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    Aerodynamic characteristics of horizontal tail surfaces (1940)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Collected data are presented on the aerodynamic characteristics of 17 horizontal tail surfaces including several with balanced elevators and two with end plates. Curves are given for coefficients of normal force, drag, and elevator hinge moment. A limited analysis of the results has been made. The normal-force coefficients are in better agreement with the lifting-surface theory of Prandtl and Blenk for airfoils of low aspect ratio than with the usual lifting-line theory. Only partial agreement exists between the elevator hinge-moment coefficients and those predicted by Glauert's thin-airfoil theory.
    Type: NACA-TR-688
    Format: application/pdf
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  • 8
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    Aerodynamic Characteristics of a 4-engine Monoplane Showing Comparison of Air-cooled and Liquid-cooled Engine Installations (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-WR-L-471
    Format: application/pdf
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  • 9
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    Design charts for predicting downwash angles and wake characteristics behind plain and flapped wings (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Equations and design charts are given for predicting the downwash angles and the wake characteristics for power-off conditions behind plain and flapped wings of the types used in modern design practice. The downwash charts cover the cases of elliptical wings and wings of taper ratios 1, 2, 3, and 5, with aspect ratios of 6, 9, and 12, having flaps covering 0, 40, 70, and 100 percent of the span. Curves of the span load distributions for all these cases are included. Data on the lift and the drag of flapped airfoil sections and curves for finding the contribution of the flap to the total wing lift for different types of flap and for the entire range of flap spans are also included. The wake width and the distribution of dynamic pressure across the wake are given in terms of the profile-drag coefficient and the distance behind the wing. A method of estimating the wake position is also given. The equations and charts are based on theory that has been shown in a previous report to be in agreement with experiment.
    Type: NACA-TR-648
    Format: application/pdf
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  • 10
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    Determination of Boundary-Layer Transition on Three Symmetrical Airfoils in the NACA Full-Scale Wind Tunnel (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For the purpose of studying the transition from laminar to turbulent flow, boundary-layer measurements were made in the NACA full-scale wind tunnel on three symmetrical airfoils of NACA 0009, 0012, and 0018 sections. The effects of variations in lift coefficient, Reynolds number, and airfoil thickness on transition were investigated. Air speed in the boundary layer was measured by total-head tubes and by hot wires; a comparison of transition as indicated by the two techniques was obtained. The results indicate no unique value of Reynolds number for the transition, whether the Reynolds number is based upon the distance along the chord or upon the thickness of the boundary layer at the transition point. In general, the transition is not abrupt and occurs in a region that varies in length as a function of the test conditions.
    Type: NACA-TR-637
    Format: application/pdf
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