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  • 1
    facet.materialart.
    Unknown
    Effect of the Surface Condition of a Wing on the Aerodynamic Characteristics of an Airplane (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to determine the effect of the surface conditions of a wing on the aerodynamic characteristics of an airplane, tests were conducted in the N.A.C.A. full-scale wind tunnel on the Fairchild F-22 airplane first with normal commercial finish of wing surface and later with the same wing polished. Comparison of the characteristics of the airplane with the two surface conditions shows that the polish caused a negligible change in the lift curve, but reduced the minimum drag coefficient by 0.001. This reduction in drag if applied to an airplane with a given speed of 200 miles per hour and a minimum drag coefficient of 0.025 would increase the speed only 2.9 miles per hour, but if the speed remained the same, the power would be reduced 4 percent.
    Type: NACA-TN-495
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Drag of Prestone and Oil Radiators on the YO-31A Airplane (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: At the request of the Army Air Corps tests were conducted on a mock-up of the YO-31A airplane to determine the drag of the prestone and oil radiators. The drag of the airplane was determined with both radiators exposed on the lower surface of the fuselage; with each radiator exposed; and with no radiators. The results show that at 120 m.p.h the oil radiator accounted for 2.8 percent of the drag of the complete airplane; the prestone radiator 8.3 percent; and both radiators together, 11.8 percent.
    Type: NACA-TN-549
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Pressure Distribution on the C-7 Airship (1926)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made for the purpose of determining the aerodynamic pressure distribution encountered on a "C" class airship in flight. It was conducted in two parts: (a) tests on the tail surfaces in which the pressures at 201 points were measured and (b) tests on the envelope in which 190 points were used, both tests being made under as nearly identical flight conditions as possible, so that the results could be combined and the pressure distribution over the entire airship obtained.
    Type: NACA-TR-223
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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