15.2.9. Reduction Factors Due to Cladding

Reference: Abbott, Richard. Analysis and Design of Composite and Metallic Flight Vehicle Structures 3 Edition, 2019.

 (NACA-TN-3781, 1957) is the best available reference (again) and gives a simple rational method for how to account for the presence of cladding.

Figure 15.2.9‑1: Cross Section of a Clad Plate  (NACA-TN-3781, 1957)

The reducing in buckling due to the presence of cladding depends on two ratios:

For different loading conditions and stress level the following terms apply.

Figure 15.2.9‑2: Reduction Factors Due to Cladding  (NACA-TN-3781, 1957)
Figure 15.2.9‑3: Cladding of Thicknesses  (NACA-TN-3781, 1957)

This method is available in this spreadsheet:

AA-SM-007-060 Buckling Reduction Factors due to Cladding

Note that in some circumstances, particularly for panels with low buckling allowables, a cladding reduction factor of greater than 1.00 can occur. In this circumstance a maximum value of 1.00 should be used.

15.2.9. Reduction Factors Due to Cladding

Reference: Abbott, Richard. Analysis and Design of Composite and Metallic Flight Vehicle Structures 3 Edition, 2019.

 (NACA-TN-3781, 1957) is the best available reference (again) and gives a simple rational method for how to account for the presence of cladding.

Figure 15.2.9‑1: Cross Section of a Clad Plate  (NACA-TN-3781, 1957)

The reducing in buckling due to the presence of cladding depends on two ratios:

For different loading conditions and stress level the following terms apply.

Figure 15.2.9‑2: Reduction Factors Due to Cladding  (NACA-TN-3781, 1957)
Figure 15.2.9‑3: Cladding of Thicknesses  (NACA-TN-3781, 1957)

This method is available in this spreadsheet:

AA-SM-007-060 Buckling Reduction Factors due to Cladding

Note that in some circumstances, particularly for panels with low buckling allowables, a cladding reduction factor of greater than 1.00 can occur. In this circumstance a maximum value of 1.00 should be used.