Consider an infinitely thin flat plate of chord c at an angle of attack α in a supersonic flow. The pressure on the upper and lo
wer surfaces are different but constant over each surface; that is, pu(s) = C1 and pl(s) = C2, where C1 and C2 are constants and C2 > C1. Ignoring the shear stress, calculate the location of the center of pressure.
1 answer:
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Answer:
7.07%
Explanation:
Thermal efficiency can be by definition seen as the ratio of the heat utilized by a heat engine to the total heat units in the fuel consumed.
We will determine the thermal efficiency of the given problem at the attached file.
Answer:
Check the explanation
Explanation:
Code in C++::
#include <iostream>
using namespace std;
void PrintFactorial(int factCounter, int factValue){
int nextCounter = 0;
int nextValue = 0;
if (factCounter == 0) { // Base case: 0! = 1
cout << "1" << endl;
}
else if (factCounter == 1) { // Base case: Print 1 and result
cout << factCounter << " = " << factValue << endl;
}
else { // Recursive case
cout << factCounter << " * ";
nextCounter = factCounter - 1;
nextValue = nextCounter * factValue;
/* Your solution goes here */
/**
* We just need to call the function PrintFactorial() recursively
* and pass the two parameters that are just calculated as nextCounter for factCounter
* and nextValue as factValue.
*/
PrintFactorial(nextCounter,nextValue);
}
}
int main() {
int userVal = 0;
userVal = 5;
cout << userVal << "! = ";
PrintFactorial(userVal, userVal);
return 0;
}
Output::
Test Case 1 where userVal=5::
<em><u>Attached Image 1</u></em>
Test Case 2 where userVal=6::
<em><u>Attached Image 1</u></em>
