An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x lO 6 and 5.6 x l06 to determine the pres-sure distributions over a swept wing with a series of 14 control con-figurations. The wing had 40 ° of sweep of the quarter-chord line, an aspect ratio of 5.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 ° to +15 ° for control deflections from-60 ° to 60 °. This report contains tabulated pressure data for the complete range of test conditions. _A __j
Flight tests were conducted to determine the pressure distribution over the wing of a swept-wing jet...
Performance test data for pressure distributions over 60 deg delta wing at Mach 1.61 and 2.0
Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings o...
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and w...
An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers from 1.7 X 10 t...
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...
Experimental investigations have been made of the now characteristics on wings of moderate sweepbac...
Pressure distributions and wake measurements have been obtained for wings with 300 and 11.50 of swee...
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution ...
Analyses have been conducted of wing pressure distribution and boundary layer data obtained from fli...
A loads investigation was made with flap spoiler ailerons, deflec-tor ailerons, and a spoiler-slot-d...
"NASA TN D-236.""Langley Research Center, Langley Field, Va.""April 1960."Cover title.Includes bibli...
This report presents comprehensive pressure-distribution measurements on four (4) swept-back wings (...
AbstractA series of wind tunnel tests are performed to examine the flow field over a swept wing unde...
Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings o...
Flight tests were conducted to determine the pressure distribution over the wing of a swept-wing jet...
Performance test data for pressure distributions over 60 deg delta wing at Mach 1.61 and 2.0
Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings o...
Pressure distributions are presented on four wings: an untwisted wing to serve as a reference, and w...
An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers from 1.7 X 10 t...
Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number...
Experimental investigations have been made of the now characteristics on wings of moderate sweepbac...
Pressure distributions and wake measurements have been obtained for wings with 300 and 11.50 of swee...
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution ...
Analyses have been conducted of wing pressure distribution and boundary layer data obtained from fli...
A loads investigation was made with flap spoiler ailerons, deflec-tor ailerons, and a spoiler-slot-d...
"NASA TN D-236.""Langley Research Center, Langley Field, Va.""April 1960."Cover title.Includes bibli...
This report presents comprehensive pressure-distribution measurements on four (4) swept-back wings (...
AbstractA series of wind tunnel tests are performed to examine the flow field over a swept wing unde...
Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings o...
Flight tests were conducted to determine the pressure distribution over the wing of a swept-wing jet...
Performance test data for pressure distributions over 60 deg delta wing at Mach 1.61 and 2.0
Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings o...
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