Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing

Wind-tunnel investigation of effects of a pusher propeller on lift, profile drag, pressure distribution, and boundary-layer transition of a flapped wing

Date: April 1, 1945
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect on transonic and supersonic drag of a fuselage protuberance of an essential unswept wing-fuselage combination

Effect on transonic and supersonic drag of a fuselage protuberance of an essential unswept wing-fuselage combination

Date: January 5, 1954
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of several aileron configurations on a tapered wing having 42.7 degrees sweepback

Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of several aileron configurations on a tapered wing having 42.7 degrees sweepback

Date: January 11, 1949
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of fullspan, 0.2 chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, taper, aspect ratio, and section-thickness ratio

Free-flight investigation of fullspan, 0.2 chord plain ailerons at high subsonic, transonic, and supersonic speeds to determine some effects of wing sweepback, taper, aspect ratio, and section-thickness ratio

Date: August 13, 1947
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of the rolling effectiveness of several delta wing : aileron configurations at transonic and supersonic speeds

Free-flight investigation of the rolling effectiveness of several delta wing : aileron configurations at transonic and supersonic speeds

Date: August 27, 1948
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a 42.7 degree sweptback wing having partial-span ailerons

Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a 42.7 degree sweptback wing having partial-span ailerons

Date: October 25, 1948
Creator: Sandahl, Carl A
Description: An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary free-flight investigation of the effect of airfoil section on aileron rolling effectiveness at transonic and supersonic speeds

Preliminary free-flight investigation of the effect of airfoil section on aileron rolling effectiveness at transonic and supersonic speeds

Date: June 25, 1948
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane

Free-flight investigation at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane

Date: July 21, 1948
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of the rolling effectiveness of a wing-spoiler arrangement at high subsonic, transonic, and supersonic speeds

Free-flight investigation of the rolling effectiveness of a wing-spoiler arrangement at high subsonic, transonic, and supersonic speeds

Date: May 17, 1948
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332

Date: March 16, 1950
Creator: Hall, James R.
Description: Free-flight tests have been made to determine the zero-lift drag of several configurations of the XAAM-N-2 pilotless aircraft. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing-thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8. Increasing the nose fineness ratio from 5.00 to 6.25 reduced the drag coefficient of the wingless models a maximum of about 0.030 (10 percent) at M = 2.0. A corresponding change in nose shape for the winged models decreased the drag coefficient by about 0.05 in the Mach number range from 1.1 to 1.4; at Mach numbers greater than 1.6 no measurable reduction in drag coefficient was obtained. The drag of the present Sparrow fuselage is less than that of a parabolic fuselage which could contain the same equipment.
Contributing Partner: UNT Libraries Government Documents Department
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