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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Confidential Bulletins
 Collection: National Advisory Committee for Aeronautics Collection
Condensation trails : where they occur and what can be done about them
No Description digital.library.unt.edu/ark:/67531/metadc61828/
Construction of finned aluminum muffs for aircraft engine cylinder barrels
No Description digital.library.unt.edu/ark:/67531/metadc61901/
The effect of spinner-body gap on the pressures available for cooling in the NACA E-type cowling
No Description digital.library.unt.edu/ark:/67531/metadc62103/
Interference effects of longitudinal flat plates on low-drag airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61370/
Investigation of effects of various camouflage paints and painting procedures on the drag characteristics of an NACA 65(sub 421)-420, a = 1.0 airfoil section
No Description digital.library.unt.edu/ark:/67531/metadc61395/
Investigation of extreme leading-edge roughness on thick low-drag airfoils to indicate those critical to separation
No Description digital.library.unt.edu/ark:/67531/metadc61332/
Investigation of the variation of lift coefficient with Reynolds number at a moderate angle of attack on a low-drag airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61298/
NACA Confidential Bulletins
No Description digital.library.unt.edu/ark:/67531/metadc53331/
Notes on the effects of trailing-edge shapes of low-drag airfoils on profile drag and the trim and balance of control surfaces
No Description digital.library.unt.edu/ark:/67531/metadc61330/
Preliminary experimental investigation of airfoils in cascade
No Description digital.library.unt.edu/ark:/67531/metadc61400/
A preliminary study of the effect of compressive load on the fairness of a low-drag wing specimen with Z-section stiffeners
No Description digital.library.unt.edu/ark:/67531/metadc61311/
Some lift and drag measurements of a representative bomber nacelle on a low-drag wing I
No Description digital.library.unt.edu/ark:/67531/metadc62112/
Some lift and drag measurements of a representative bomber nacelle on a low-drag wing II
No Description digital.library.unt.edu/ark:/67531/metadc62114/
Variation with Mach Number of Static and Total Pressures Through Various Screens
Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which can be computed, is reached. Since choking imposes a restriction on the mass rate of flow and maximum losses are incurred at this condition, great care must be taken in selecting the screen mesh and wire dimmeter for an installation so that the choking Mach number is. digital.library.unt.edu/ark:/67531/metadc62531/