Report presents the results of a pressure-distribution investigation conducted in the Langley Memorial Aeronautical Laboratory 7 by 10-foot wind tunnel to determine the air loads on an NACA 23012 airfoil in combination with a fixed leading-edge slot and a slotted flap. Pressures were measured over the upper and lower surfaces of the component parts of the combination for several angles of attack and at several flap settings. The data, presented as pressure diagrams and graphs of section coefficients, are applicable to rib, slat, and flap designs for the combination.
Pressure distribution over an NACA 23012 airfoil with a fixed slot and a slotted flap
01.01.1942
Sonstige
Keine Angabe
Englisch
Pressure distribution over NACA 23012 airfoil with fixed slot and slotted flap
Engineering Index Backfile | 1942
|Pressure distribution over N.A.C.A. 23012 airfoil with slotted and plain flap
Engineering Index Backfile | 1938
|Pressure distribution over N.A.C.A. 23012 airfoil with slotted and plain flap
Engineering Index Backfile | 1938
|Pressure distribution over N.A.C.A. 23012 airfoil with N.A.C.A. 23012 external-airfoil flap
Engineering Index Backfile | 1938
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