5 research outputs found
Preliminary Wind-Tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92
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NACA Research Memorandums
Report presenting the damping-in-roll coefficients for a series of thin triangular plan-form wings and two rectangular wings in the 9-inch supersonic wind tunnel. The damping in roll of the rectangular wings was very close to what was predicted by linear theory, but the triangular wings gave results approximately 10 percent below that predicted when the wing leading edges were well ahead of or behind the Mach cone
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NACA Research Memorandums
Report presenting experimental damping-in-roll derivatives obtained for a series of 33 swept and tapered wings. The wing plan forms were selected so that a range of leading-edge positions ahead of and behind the Mach cone obtained at three Mach numbers
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NACA Technical Notes
Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92