National Advisory Committee for Aeronautics (NACA) - 8 Matching Results

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Comparison between flight-measured and calculated span load distribution at high Mach numbers

Description: Report presenting an analysis of the spanwise loading using two different methods on the wing of an airplane for which pressure-distribution measurements were available from flight tests up to a Mach number of 0.866. A comparison between measured and calculated distributions was made on the basis of equal wing-panel normal-force coefficients.
Date: November 26, 1947
Creator: Rolls, L. Stewart
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of a Fuselage and Various High-Lift and Stall-Control Flaps on Aerodynamic Characteristics in Pitch of an NACA 64-Series 40 Degree Swept-Back Wing

Description: Report presenting wind-tunnel testing to determine the low-speed lift, drag, and pitching-moment characteristics of a 40 degree sweptback wing with high-lift and stall-control flaps and a fuselage with a fineness ratio of 10.2 to 1. Low, medium, and high-wing-fuselage combinations were tested at high Reynolds numbers. Results regarding the high-lift and stall-control flaps and wing-fuselage combinations are provided.
Date: May 26, 1947
Creator: Conner, D. William & Neely, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 24, 1946 to August 6, 1946 at Orlando, Florida

Description: The results obtained from gust and draft velocity measurements within thunderstorms for the period July 24, 1946 to August 6, 1946 at Orlando, Florida are presented herein. These data are summarized in tables I and II and are of the type presented in reference 1 for previous flights. In two thunderstorm traverses, indications of ambient-air temperature were obtained from photo-observer records. These data are summarized in table III.
Date: March 26, 1947
Creator: Tolefson, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Further investigation of NACA 4-(5)(08)-03 two-blade propeller at high forward speeds

Description: Report presenting tests of an NACA 4-(5)(08)-03 two-blade propeller in the 8-foot high-speed tunnel for blade angles of 45 and 60 degrees extending the Mach number range from that of previous tests of the propeller up to Mach number 0.913. When the forward speed was increased from a low value to a forward Mach number of 0.90, the loss in peak efficiency was found to be not more than 47 percent.
Date: May 26, 1947
Creator: Carmel, Melvin M. & Robinson, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Minimum Specific Fuel Consumption of a Liquid-Cooled Multicylinder Aircraft Engine as Affected by Compression Ratio and Engine Operating Conditions

Description: From Summary: "An investigation was conducted on a 12-cylinder V-type liquid-cooled aircraft engine of 1710-cubic-inch displacement to determine the minimum specific fuel consumption at constant cruising engine speed and compression ratios of 6.65, 7.93, and 9.68. At each compression ratio, the effect.of the following variables was investigated at manifold pressures of 28, 34, 40, and 50 inches of mercury absolute: temperature of the inlet-air to the auxiliary-stage supercharger, fuel-air ratio… more
Date: February 26, 1947
Creator: Brun, Rinaldo J.; Feder, Melvin S. & Harries, Myron L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Tank Tests of NACA Hydro-Skis for High-Speed Airplanes

Description: Report presenting the results from tank landing and take-off tests with a dynamic model of a hypothetical jet-propelled airplane equipped with NACA hydro-skis. Results regarding landing tests, take-off tests, and practical considerations for the creation of hydro-ski configurations are provided. The hydro-skis suitable for flush retraction into streamline fuselages do appear to offer a practical means of water take-offs and landings.
Date: November 26, 1947
Creator: Dawson, John R. & Wadlin, Kenneth L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag

Description: Report presenting flight tests of rocket-powered models at supersonic speeds to determine the effect of nose fineness ratio of winged bodies on total and component drag at high Mach numbers. Wingless models of three nose fineness ratios and winged models of two nose fineness ratios flown through a range of Mach numbers. Results regarding total drag, body drag, and wing drag are provided.
Date: June 26, 1947
Creator: Katz, Ellis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Spin and Recovery Characteristics of the Curtiss-Wright XP-87 Airplane

Description: "The spin and recovery characteristics of the Curtiss-Wright XP-87 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape, are presented in this report. The characteristics were estimated rather than determined by model tests because the XP-87 dimensional and mass characteristics were considered to be noncritical and because data were available from model tests of se… more
Date: May 26, 1947
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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