Add to ORKGReport presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to determine the effect of the deflection of main and auxiliary slotted flaps on the aerodynamic section characteristics of large-chord NACA 23012, 23021, 23030 airfoils equipped with 40-percent-chord double slotted flaps. The complete aerodynamic section characteristics and envelope polar curves are given for each airfoil-flap combination. The effect of airfoil thickness is shown, and comparisons are made of single slotted flaps with double slotted flaps on each of the airfoils
A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section...
Report presents the results of an investigation conducted in the Langley 19-foot pressure tunnel to ...
Report presents the results of a pressure-distribution investigation conducted in the Langley Memori...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-c...
AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord s...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 27-212 ai...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a large...
An investigation has been made in the N.A.C.A. 7- by 10-foot wind tunnel of a large-chord N.A.C.A. 2...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the effect of slot-lip ...
An investigation was made in the 7 by 10-foot wind tunnel and in the variable-density wind tunnel of...
Report presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to det...
Report presents the results of an investigation of the general aerodynamic characteristics of the NA...
Report presents an investigation carried out in the NACA 7- by 10-foot wind tunnel of an NACA 23012 ...
A pressure-distribution investigation has been conducted in the NACA 4 by 6-foot vertical wind tunne...
A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section...
Report presents the results of an investigation conducted in the Langley 19-foot pressure tunnel to ...
Report presents the results of a pressure-distribution investigation conducted in the Langley Memori...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-c...
AN investigation was made of a large-chord NACA 23030 airfoil with a 40- and a 25.66 percent-chord s...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 27-212 ai...
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a large...
An investigation has been made in the N.A.C.A. 7- by 10-foot wind tunnel of a large-chord N.A.C.A. 2...
An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large chord NACA 23021 air...
An investigation was made in the NACA 7- by 10-foot wind tunnel to determine the effect of slot-lip ...
An investigation was made in the 7 by 10-foot wind tunnel and in the variable-density wind tunnel of...
Report presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to det...
Report presents the results of an investigation of the general aerodynamic characteristics of the NA...
Report presents an investigation carried out in the NACA 7- by 10-foot wind tunnel of an NACA 23012 ...
A pressure-distribution investigation has been conducted in the NACA 4 by 6-foot vertical wind tunne...
A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section...
Report presents the results of an investigation conducted in the Langley 19-foot pressure tunnel to ...
Report presents the results of a pressure-distribution investigation conducted in the Langley Memori...