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Near-term missions to Mars may not be possible with current deployable decelerator technology. This possibility becomes a certainty for the more distant human-precursor missions. Inflatable Aerodynamic Decelerators (IADs) are a candidate technology that may provide the needed drag augmentation to enable these much heavier missions. The attached isotensoid is one of the IAD configurations favored for application at Mars. Assessing the isotensoid's technical feasibility for Mars missions requires several performance models capable of providing reasonably accurate predictions of key design parameters. This paper describes engineering-level models derived from past isotensoid technology development efforts that have been modified or improved for the problem at hand. Easily implemented models of the isotensoid inflation history, aerothermodynamic environment, and thermostructural performance are described.