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program AerodynamicCoefficients implicit none

real :: dragForce, liftForce, airDensity, velocity, referenceArea, dragCoefficient, liftCoefficient

! Input values airDensity = 1.225 ! Air density in kg/m^3 velocity = 100.0 ! Velocity in m/s referenceArea = 1.0 ! Reference area in square meters

! Calculate drag force and lift force (you need to replace these formulas with actual calculations) dragForce = 0.5 * airDensity * velocity2 * referenceArea * dragCoefficient liftForce = 0.5 * airDensity * velocity2 * referenceArea * liftCoefficient

! Calculate drag and lift coefficients dragCoefficient = dragForce / (0.5 * airDensity * velocity2 * referenceArea) liftCoefficient = liftForce / (0.5 * airDensity * velocity2 * referenceArea)

! Output the results write(,) "Drag Force: ", dragForce, " N" write(,) "Lift Force: ", liftForce, " N" write(,) "Drag Coefficient: ", dragCoefficient write(,) "Lift Coefficient: ", liftCoefficient

end program AerodynamicCoefficients

Created on November 3, 2023 12:46:41 by Anonymous Coward (197.203.87.224) (1054 characters / 0.0 pages)

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