Team Members:Yuri AmbrosioVictor AvillaTory JohansonTrevor HowardZander Skwark

Aircraft Name:To be determined

List of Requirements with Values: English (ft and s) Metric (km and hr) Standard (kt and nm)1) Level Speed 365 400 2162) Range 1.21E+10 3,700 19983) Service Ceiling 21,000 6.401 3.464) Rate of Climb (RoC) 28.92 31.73 17.135) Stalling Speed 127 139 756) Landing Distance 1,312 0.4 0.2167) Takeoff Distance 1,312 0.4 0.216

Our Personalized Constraints:4 Passengers2 Crew MembersShooting for Turboprop

Weight Ratios ValuesW1/Wo 0.97W2/W1 0.985W4/W3 1W5/W4 0.995Note: Will not change in any future itterations

L/D Ratio ValueL/D 14Note: Will change in future itterations

Prop Efficiency Value

0.85Note: Will change in future itterations

Specific Fuel Consumption Valuec (lb/(hr hp)) 0.4c(kg/(N m)) 6.76199E-08Note: Will change in future itterations

Weight of each Person and Baggage (kg) ValueWper 90Wbag 10Note: Will not change in any future itterations

Computing Wc (2 People) and Wp (4 People) ValueWc (kg) 200Wp (kg) 400

Computing W2/W3 using Range Equation ValueW2/W3 1.02124725

Computing W5/W0 using W Expansion ValueW5/W0 0.9308938164

Computing Wf/W0 with 6% of Fuel in Tank ValueWf/W0 0.0732525546

Computing W0 by Given Eqaution in Notes (kg) ValueW0 1956.0065098

Computing Wf using W Expansion (kg) ValueWf 143.28247374

Specific Weight of Fuel Value

ηpr

5.64

675.8412Note: Will not change in any future itterations

Computing Volume of Tank (m^3) ValueVtank 0.2120061247

Computing W3 Estimate by Expansion ValueW3 1829.9842862

γf (lb/gal)

γf (kg/m^3)

Part 1: Using Vstall to get (W/S)1Wing Root Airfoil NACA Value

23016.5

Wing Tip Airfor NACA Value23010.5

Computing Cl,max (Root and Tip) ValueCl,max,r 0.3Cl,max,t 0.3Note: Will change in future itterations

Computing Del Cl flap from Given Equation Value

0slope 0Del Cl 0Note: Will change in future itterations

Computing Cl,max from Given Equation ValueCl,max 0.3Note: Will change in future itterations

Computing CL,max (Historical) ValueCL,max 0.27Note: Will change in future itterations

From engineeringtoolbox.com and Valueinterpolation, density is computed

0.63199

Getting Vstall from Requirement (2) ValueVstall (m/s) 38.61111111

Computing (W/S)1 from Given Equation Value(W/S)1 127.1945707

Computing the Value of PI ValuePi 3.141592654

From Sheet 1, Know W3 Estimate ValueW3 (kg) 1829.984286Note: If this changes in Sheet 1, needs to beupdated here.

α(deg)

ρ(kg/m^3)

Computing S Using W3 and (W/S)1 ValueS1 14.38728301

Part2: Using Landing Distance to get (W/S)2Computing Va ValueVa (m/s) 50.19444

Computing Velocity Touchdown Value44.40278

Computing Average Velocity Value47.29861

Parameter of L/W ValueL/W 3.2Note: Will change in future itterations

Computing Radius of Arc ValueR (m) 103.6585

Parameter of Approach Angle Value

3Note: Will not change in any future itterations

Computing hf from Given Equation Valuehf (m) 0.14206

Computing Sa from Given Equation ValueSa (m) 288.0858

Computing Sf from Given Equation Value

Sf (m) 5.425069

Computing Sg from Landing Distance Requirement ValueSg (m) 106.4891

Parameter for Response time of applying Brakes ValuetR (s) 3

Valueμr (Concrete) 0.65

Computing (W/S)2 from Given Equation ValueNote: In the form of quadratica 1.215456b 11.81128c -106.4891

VTD (m/s)

Vave (m/s)

Ѳa (deg)

Parameter of μr

(W/S)2 with positive value in quadratic 5.687314(W/S)2 with negative value in quadratic -15.40489

Computing S Using W3 and (W/S)2 ValueS2 321.766

Part 1: Using Takeoff Distance to get (T/W)1Computing Cl,max (Root and Tip) ValueCl,max,r 0.3Cl,max,t 0.3Note: Will change in future itterations

Computing Del Cl flap from Given Equation Value

20slope 0.02Del Cl 0.4Note: Will change in future itterations

Computing Cl,max from Given Equation ValueCl,max 0.7Note: Will change in future itterations

Computing CL,max (Historical) ValueCL,max 0.63Note: Will change in future itterations

From engineeringtoolbox.com and Valueinterpolation, density is computed

0.63199

(W/S)1 from Sheet 2. Value(W/S)1 127.1947Note: If this changes in Sheet 2, needs to be updated here.

Calculating Vstall from Given Equation ValueVstall (m/s) 15.92446

Parameter of L/W ValueL/W 3.2Note: Will change in future itterations

Calculating Radius from Given Equation ValueR (m) 15.53937

Computing the Value of PI ValuePi 3.141593

Calculating Takeoff Angle from Given Equation Value

1.55153

α(deg)

ρ(kg/m^3)

ѲTO (Radians)

88.89612

Calculating Sa from Given Equation ValueSa (m) 15.53648

From Requirements, Know Takeoff Distance ValueTakeoff Distance (m) 400

Calculating Sg from Given Equation ValueSg (m) 384.4635

Calculating (T/W)1 from Given Equation Value(T/W)1 0.10249

Know Wf Estimate from Sheet 1 ValueWf (kg) 143.2825Note: If this changes in Sheet 1, needs to be updated here.

Calculating Thurst 1 from Ratio and Wf ValueT1 (N) 14.68495

Calculating Power Available ValuePa1 (J/s) 268.9274

Prop Efficiency Value

0.85Note: Will change in future itterations

Calculating Shaft Power ValueP1 (J/s) 316.3852

ѲTO (Degrees)

ηpr

Part 2: Using Rate of Climb to get (T/W)2Given Reynolds Number ValueRe 1.00E+06Note :Will change in future itterations

Calculating Cf from Given Equaiton ValueSqrt value 1000

Cf 0.001328

Calculating Drag Coefficient ValueCdo 0.005312

Know estimate of L/D max from Sheet 1 ValueL/D max 14Note: Will change in future itterations

Calculating K Value ValueK 0.240119

Solving for Wing Efficiency when AR=7.5 Value0.573241

Value

AR 2.209393

Note: Can play with both of these to getgood combingation. As of now, will use

From Requirements, Know Rate of Climb ValueR/C (m/s) 8.813889

Calculating Shaft Power ValueInterier Square Root term 3.881712Exterior Square Root term 39.52811Right Hand Side of Equation 12.07496P2 (J/s) 2035.447

eo

Solving for Aspect Ratio when eo=.6

value of eo=.6 solving for AR

Part 3: Using Maximum Speed at Mid-Cruise to get (T/W)3Weight Ratios ValuesW1/Wo 0.97W2/W1 0.985W4/W3 1W5/W4 0.995Note: Will not change in any future itterations

Calculating the Weight Ratio of W2/W0 ValueW2/Wo 0.95545

From Sheet 1, Know Wo ValueWo (kg) 1956.007Note: If this changes in Sheet 1, needs to be updated here

Calculating W2 ValueW2 (kg) 1868.866

From Sheet 1, Know (W2/W3) ValueW2/W3 1.021247Note: If this changes in Sheet 1, needs to be updated here

Value

1849.425

From Requirements, Know Vmax (Level Speed) ValueVmax (m/s) 111.1111

From Sheet 2, Know S1 ValueS1 14.38728Note: If this changes in Sheet 2, needs to be updated here

ValueFirst term of Right Hand Side 0.161211Second term of Right Hand Side 0.007912

0.169123

Calculating Shaft Power ValueP3 (J/s) 40886.38

Therefore, Largest Value is P3 ValueP3(J/s) 40886.38

Calculating WMC from Given Equation

WMC (kg)

Calculating T/WMC

T/WMC

Wingspan 249.48 % NACA 23016 Root %NACA 23010 tip% chord=44.5 in % Chord=26in% x y z % x y z

44.5 0.0748 0 26 0.0273 249.4844.3879 0.0983 0 25.9345 0.0364 249.4844.1845 0.1406 0 25.8157 0.0528 249.4843.9237 0.1945 0 25.6633 0.0738 249.4843.6185 0.2572 0 25.4849 0.0983 249.4843.2754 0.3271 0 25.2845 0.1253 249.4842.9007 0.4027 0 25.0656 0.155 249.4842.4971 0.4837 0 24.8297 0.1862 249.4842.0685 0.5687 0 24.5794 0.2194 249.4841.6168 0.6573 0 24.3155 0.254 249.4841.1451 0.7485 0 24.0399 0.2896 249.4840.6543 0.8428 0 23.7531 0.3263 249.4840.1466 0.939 0 23.4564 0.364 249.4839.6232 1.0373 0 23.1507 0.4022 249.4839.0857 1.1365 0 22.8366 0.4412 249.4838.5352 1.2371 0 22.515 0.4807 249.4837.9727 1.339 0 22.1863 0.5205 249.4837.3991 1.4409 0 21.8512 0.5606 249.4836.8162 1.5437 0 21.5106 0.6009 249.4836.2234 1.6465 0 21.1643 0.6412 249.4835.6227 1.7489 0 20.8133 0.6817 249.4835.0148 1.8516 0 20.4581 0.722 249.4834.3998 1.954 0 20.0988 0.7623 249.4833.7786 2.0555 0 19.7358 0.8024 249.4833.1525 2.1565 0 19.37 0.8424 249.4832.5215 2.2566 0 19.0013 0.8819 249.4831.8865 2.3558 0 18.6303 0.9212 249.4831.2479 2.4537 0 18.2572 0.9602 249.4830.6062 2.5507 0 17.8823 0.9987 249.4829.9623 2.646 0 17.5061 1.0366 249.4829.3162 2.7399 0 17.1285 1.0741 249.4828.6691 2.832 0 16.7505 1.1107 249.4828.0208 2.9228 0 16.3717 1.1469 249.4827.3719 3.0113 0 15.9926 1.1825 249.4826.7231 3.0976 0 15.6135 1.2171 249.4826.0748 3.1822 0 15.2347 1.2511 249.4825.4277 3.2641 0 14.8567 1.2841 249.4824.7816 3.3437 0 14.4791 1.3164 249.4824.1368 3.4207 0 14.1024 1.3478 249.4823.4947 3.4955 0 13.7272 1.378 249.4822.8548 3.5671 0 13.3533 1.4074 249.4822.2175 3.6361 0 12.981 1.4355 249.4821.5838 3.702 0 12.6108 1.4628 249.4820.9537 3.7647 0 12.2426 1.4885 249.4820.3272 3.8239 0 11.8765 1.5135 249.48

19.705 3.8804 0 11.5131 1.5369 249.4819.0874 3.9329 0 11.1522 1.5592 249.4818.4751 3.9823 0 10.7944 1.58 249.4817.8676 4.0277 0 10.4395 1.5998 249.4817.2656 4.07 0 10.0877 1.618 249.4816.6697 4.1078 0 9.7396 1.6346 249.4816.0801 4.1421 0 9.3951 1.65 249.4815.4967 4.1723 0 9.0542 1.6637 249.4814.9204 4.1981 0 8.7175 1.6762 249.4814.3508 4.2204 0 8.3847 1.6869 249.4813.7888 4.2377 0 8.0564 1.6962 249.4813.2339 4.2515 0 7.7321 1.7038 249.4812.6874 4.2604 0 7.4129 1.7098 249.4812.1489 4.2653 0 7.0983 1.7142 249.48

11.619 4.2658 0 6.7886 1.7168 249.4811.0974 4.2618 0 6.4839 1.7178 249.4810.5852 4.2533 0 6.1846 1.7173 249.4810.0819 4.2404 0 5.8906 1.715 249.48

9.588 4.223 0 5.602 1.7111 249.489.1038 4.2012 0 5.3191 1.7053 249.488.6299 4.1745 0 5.0422 1.6981 249.488.1657 4.1429 0 4.771 1.6887 249.487.7123 4.1056 0 4.5061 1.6767 249.487.2695 4.062 0 4.2474 1.6619 249.486.8374 4.0112 0 3.9949 1.644 249.486.4169 3.9529 0 3.7492 1.6227 249.486.0071 3.8871 0 3.5097 1.5977 249.485.6092 3.8137 0 3.2773 1.5691 249.485.2234 3.7322 0 3.0519 1.5369 249.484.8492 3.6432 0 2.8332 1.501 249.484.4874 3.5462 0 2.6218 1.4612 249.484.1381 3.4416 0 2.4177 1.418 249.483.8012 3.3295 0 2.2209 1.3712 249.483.4772 3.2107 0 2.0316 1.3211 249.483.1666 3.0852 0 1.8502 1.2678 249.482.8689 2.9535 0 1.6762 1.2116 249.48

2.585 2.816 0 1.5103 1.1528 249.482.3144 2.6731 0 1.3523 1.092 249.482.0581 2.5258 0 1.2025 1.0288 249.481.8156 2.3741 0 1.0608 0.9638 249.481.5878 2.2192 0 0.9277 0.8975 249.481.3742 2.0612 0 0.8029 0.8304 249.481.1752 1.901 0 0.6867 0.7623 249.48

0.991 1.7395 0 0.579 0.6939 249.480.8219 1.5766 0 0.4802 0.6256 249.480.6684 1.4133 0 0.3905 0.5572 249.48

0.53 1.25 0 0.3097 0.4896 249.480.4072 1.0871 0 0.2379 0.423 249.48

0.3004 0.9256 0 0.1755 0.3575 249.480.2092 0.7654 0 0.1222 0.2933 249.480.1344 0.6074 0 0.0785 0.2306 249.480.0756 0.4517 0 0.0442 0.17 249.480.0338 0.2982 0 0.0198 0.1113 249.480.0085 0.1477 0 0.0049 0.0546 249.48

0 0 0 0 0 249.480.0085 -0.1424 0 0.0049 -0.0515 249.480.0338 -0.2777 0 0.0198 -0.0991 249.480.0756 -0.4058 0 0.0442 -0.1433 249.480.1344 -0.5269 0 0.0785 -0.1836 249.480.2092 -0.6412 0 0.1222 -0.2205 249.480.3004 -0.7489 0 0.1755 -0.254 249.480.4072 -0.8508 0 0.2379 -0.2847 249.48

0.53 -0.9465 0 0.3097 -0.3125 249.480.6684 -1.0369 0 0.3905 -0.3375 249.480.8219 -1.1227 0 0.4802 -0.3601 249.48

0.991 -1.2033 0 0.579 -0.3806 249.481.1752 -1.2803 0 0.6867 -0.3994 249.481.3742 -1.3532 0 0.8029 -0.4165 249.481.5878 -1.4227 0 0.9277 -0.4324 249.481.8156 -1.4894 0 1.0608 -0.4469 249.482.0581 -1.5539 0 1.2025 -0.461 249.482.3144 -1.6167 0 1.3523 -0.4745 249.48

2.585 -1.6772 0 1.5103 -0.4878 249.482.8689 -1.7368 0 1.6762 -0.501 249.483.1666 -1.796 0 1.8502 -0.5145 249.483.4772 -1.8539 0 2.0316 -0.5283 249.483.8012 -1.9117 0 2.2209 -0.5429 249.484.1381 -1.9696 0 2.4177 -0.558 249.484.4874 -2.0274 0 2.6218 -0.5741 249.484.8492 -2.0853 0 2.8332 -0.591 249.485.2234 -2.1436 0 3.0519 -0.6087 249.485.6092 -2.2019 0 3.2773 -0.6274 249.486.0071 -2.2597 0 3.5097 -0.6469 249.486.4169 -2.3176 0 3.7492 -0.6672 249.486.8374 -2.375 0 3.9949 -0.6882 249.487.2695 -2.4315 0 4.2474 -0.7093 249.487.7123 -2.4867 0 4.5061 -0.7309 249.488.1657 -2.5401 0 4.771 -0.7519 249.488.6299 -2.5908 0 5.0422 -0.7725 249.489.1038 -2.638 0 5.3191 -0.792 249.48

9.588 -2.6811 0 5.602 -0.8102 249.4810.0819 -2.7203 0 5.8906 -0.8268 249.4810.5852 -2.7554 0 6.1846 -0.8421 249.4811.0974 -2.7866 0 6.4839 -0.8559 249.48

11.619 -2.8137 0 6.7886 -0.8684 249.4812.1489 -2.8364 0 7.0983 -0.8793 249.48

12.6874 -2.8556 0 7.4129 -0.8889 249.4813.2339 -2.8703 0 7.7321 -0.897 249.4813.7888 -2.8814 0 8.0564 -0.9035 249.4814.3508 -2.8885 0 8.3847 -0.909 249.4814.9204 -2.8916 0 8.7175 -0.9129 249.4815.4967 -2.8912 0 9.0542 -0.9155 249.4816.0801 -2.8867 0 9.3951 -0.9165 249.4816.6697 -2.8787 0 9.7396 -0.9165 249.4817.2656 -2.8667 0 10.0877 -0.9152 249.4817.8676 -2.8516 0 10.4395 -0.9123 249.4818.4751 -2.8329 0 10.7944 -0.9084 249.4819.0874 -2.8106 0 11.1522 -0.9035 249.48

19.705 -2.7853 0 11.5131 -0.897 249.4820.3272 -2.7563 0 11.8765 -0.8897 249.4820.9537 -2.7247 0 12.2426 -0.8809 249.4821.5838 -2.6896 0 12.6108 -0.8713 249.4822.2175 -2.6518 0 12.981 -0.8606 249.4822.8548 -2.6113 0 13.3533 -0.8486 249.4823.4947 -2.5677 0 13.7272 -0.8359 249.4824.1368 -2.5214 0 14.1024 -0.8221 249.4824.7816 -2.4729 0 14.4791 -0.8076 249.4825.4277 -2.4217 0 14.8567 -0.792 249.4826.0748 -2.3683 0 15.2347 -0.7756 249.4826.7231 -2.3127 0 15.6135 -0.7584 249.4827.3719 -2.2548 0 15.9926 -0.7405 249.4828.0208 -2.1947 0 16.3717 -0.7218 249.4828.6691 -2.1329 0 16.7505 -0.7023 249.4829.3162 -2.0692 0 17.1285 -0.6822 249.4829.9623 -2.0038 0 17.5061 -0.6614 249.4830.6062 -1.9371 0 17.8823 -0.6401 249.4831.2479 -1.8686 0 18.2572 -0.6183 249.4831.8865 -1.7987 0 18.6303 -0.5959 249.4832.5215 -1.7275 0 19.0013 -0.5728 249.4833.1525 -1.6554 0 19.37 -0.5496 249.4833.7786 -1.582 0 19.7358 -0.5257 249.4834.3998 -1.5077 0 20.0988 -0.5018 249.4835.0148 -1.4325 0 20.4581 -0.4774 249.4835.6227 -1.3568 0 20.8133 -0.4527 249.4836.2234 -1.2807 0 21.1643 -0.4277 249.4836.8162 -1.2042 0 21.5106 -0.4025 249.4837.3991 -1.1272 0 21.8512 -0.3773 249.4837.9727 -1.0506 0 22.1863 -0.352 249.4838.5352 -0.9737 0 22.515 -0.3268 249.4839.0857 -0.8976 0 22.8366 -0.3016 249.4839.6232 -0.8219 0 23.1507 -0.2764 249.4840.1466 -0.7467 0 23.4564 -0.2517 249.4840.6543 -0.6728 0 23.7531 -0.2272 249.4841.1451 -0.6003 0 24.0399 -0.2031 249.48

41.6168 -0.5296 0 24.3155 -0.1794 249.4842.0685 -0.461 0 24.5794 -0.1565 249.4842.4971 -0.3952 0 24.8297 -0.1347 249.4842.9007 -0.332 0 25.0656 -0.1136 249.4843.2754 -0.2728 0 25.2845 -0.0939 249.4843.6185 -0.218 0 25.4849 -0.0754 249.4843.9237 -0.1691 0 25.6633 -0.059 249.4844.1845 -0.1264 0 25.8157 -0.0447 249.4844.3879 -0.0934 0 25.9345 -0.0335 249.48

44.5 -0.0748 0 26 -0.0273 249.48

AR 7.5 7.077447Wingspan 675 498.96 inS 60750 35176.68 in^2Twist 0.05236

root 44.5 intip 26 in