초록 ▼

A vertical stabilizer is configured to minimize the rate of change of cross-sectional area distribution of the vehicle or device to which the vertical stabilizer is mounted. One or more "waisted" areas can be included at the tip and/or the root of the vertical stabilizers, as well as over the distan

A vertical stabilizer is configured to minimize the rate of change of cross-sectional area distribution of the vehicle or device to which the vertical stabilizer is mounted. One or more "waisted" areas can be included at the tip and/or the root of the vertical stabilizers, as well as over the distance from tip to root of the vertical stabilizer. In some situations, a strake is mounted on the vehicle or device, such as an aircraft, and the vertical stabilizer is mounted to the tip of the strake. The strake can also be area ruled with one or more "waisted" sections at the juncture of the vertical stabilizer. Applying area ruling to the vertical stabilizer helps to further reduce the drag of the vehicle or device.

대표청구항 ▼

What is claimed is: 1. A method for incorporating area ruled surfaces in a supersonic aircraft, the method comprising: specifying design constraints in an automated analysis system to minimize the change (first derivative) of cross-sectional area distribution, and rate of change (second derivative)

What is claimed is: 1. A method for incorporating area ruled surfaces in a supersonic aircraft, the method comprising: specifying design constraints in an automated analysis system to minimize the change (first derivative) of cross-sectional area distribution, and rate of change (second derivative) of cross-sectional area distribution of the aircraft; and reflecting a vertical tail fin about an inverted V-tail coupled to the vertical tail fin to simulate a symmetry boundary condition in which a degree of freedom is removed from the flowfield in order to represent the inverted V-tail channel during automated analysis. 2. The method of claim 1 further comprising: specifying design constraints in an automated analysis system to maintain maximum possible thickness of a vertical fin at a given location for structural support while achieving minimum drag and zero closure angle at the trailing edge of vertical fin. 3. The method of claim 1 further comprising: optimizing the shape of the aircraft for Mach numbers that are close to transonic conditions in order to avoid choked flow in a channel formed between the vertical tail fin and the inverted V-tail. 4. The method of claim 1 further comprising: determining a first optimum aircraft configuration for the "waisted" area of the vertical fin and aircraft fuselage along Mach angle lines at a first Mach number; determining a second optimum aircraft configuration for the "waisted" area of the vertical fin and aircraft fuselage along Mach angle lines at a second Mach number; weighting the first and second optimal aircraft configurations to form weighted configurations; and averaging the weighted configurations to determine a final configuration. 5. The method of claim 1 further comprising: determining a first optimum aircraft vertical tail configuration using a weighted combination of thicknesses and n-order derivatives as design variables in orthogonal functions and non-orthogonal functions. 6. The method according to claim 4 further comprising: determining weighting factors for the first and second optimum configurations based on a percentage of time the aircraft is expected to fly at each Mach number during typical flight profiles. 7. The method according to claim 4 further comprising: determining weighting factors for the first and second Mach numbers based on at least one of the group of: minimized drag and minimized sonic boom disturbance. 8. The method according to claim 1 further comprising: optimizing the cross-sectional area distribution along Mach angle lines of a given azimuth. 9. The method according to claim 2, further comprising: determining weighting coefficients for design variables to maintain thickness/trailing-edge closure constraints for the vertical fin. 10. The method according to claim 2, further comprising: determining the weighting coefficients for nth order derivatives with or without orthogonal functions to represent respective thickness variables. 11. The method according to claim 2, wherein the stabilizing surface is an inverted V-tail, the method further comprising: determining weighting factors based on avoiding choked flow conditions between the vertical fin and the stabilizing surface.