how to create a lifting line theory code in javascript

index.tsx
// Constants and parameters
const wingSpan = 10; // Wing span in meters
const chordLength = 1; // Chord length in meters
// ... other parameters

// Function to calculate lift coefficient at a given spanwise location
function calculateLiftCoefficient(spanwiseLocation) {
  // Implement your lift coefficient calculation here, using lift line theory equations
  // Return the lift coefficient at the specified spanwise location
  // For example:
  const localAngleOfAttack = ...; // Calculate the local angle of attack at the given spanwise location
  const liftCoefficient = ...; // Calculate the lift coefficient based on the airfoil characteristics and local angle of attack
  return liftCoefficient;
}

// Function to calculate the lift distribution along the span of the wing
function calculateLiftDistribution() {
  const numSegments = 100; // Number of segments to discretize the wing span
  const segmentLength = wingSpan / numSegments;
  let totalLiftCoefficient = 0;

  for (let i = 0; i < numSegments; i++) {
    const spanwiseLocation = i * segmentLength;
    const liftCoefficient = calculateLiftCoefficient(spanwiseLocation);
    totalLiftCoefficient += liftCoefficient;
  }

  // Display the total lift coefficient
  console.log('Total lift coefficient:', totalLiftCoefficient);
}

// Call the function to calculate the lift distribution
calculateLiftDistribution();
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