KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 200,000 Max Cl/Cd: 70.75 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135b-il-200000.txt Download as CSV file: xf-kc135b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL124.32 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5381 0.08848 0.08472 -0.0498 1.0000 0.0484
-10.250 -0.5582 0.08493 0.08111 -0.0509 1.0000 0.0484
-10.000 -0.5821 0.08252 0.07862 -0.0494 1.0000 0.0485
-9.750 -0.5996 0.08023 0.07625 -0.0469 1.0000 0.0485
-9.500 -0.6155 0.07797 0.07386 -0.0445 1.0000 0.0486
-9.250 -0.6088 0.06887 0.06493 -0.0458 1.0000 0.0498
-9.000 -0.6032 0.06552 0.06162 -0.0449 1.0000 0.0505
-8.750 -0.6045 0.06278 0.05888 -0.0430 1.0000 0.0512
-8.500 -0.6074 0.06030 0.05636 -0.0407 1.0000 0.0520
-8.250 -0.6120 0.05803 0.05405 -0.0378 1.0000 0.0532
-8.000 -0.6219 0.05621 0.05219 -0.0337 1.0000 0.0542
-7.750 -0.6364 0.05497 0.05090 -0.0288 0.9988 0.0549
-7.500 -0.6085 0.05655 0.05147 -0.0309 0.9865 0.0603
-7.250 -0.5898 0.04679 0.04195 -0.0345 0.9811 0.0631
-7.000 -0.5591 0.04359 0.03867 -0.0373 0.9755 0.0663
-6.500 -0.5047 0.03766 0.03208 -0.0406 0.9595 0.0776
-6.250 -0.4732 0.03544 0.02970 -0.0424 0.9525 0.0835
-6.000 -0.4470 0.03283 0.02680 -0.0434 0.9443 0.0929
-5.750 -0.4196 0.03095 0.02465 -0.0443 0.9361 0.1069
-5.250 -0.3430 0.02441 0.01703 -0.0435 0.9216 0.0556
-5.000 -0.3088 0.02221 0.01433 -0.0433 0.9141 0.0498
-4.750 -0.2778 0.02077 0.01274 -0.0436 0.9054 0.0496
-4.500 -0.2486 0.01933 0.01131 -0.0440 0.8972 0.0519
-4.250 -0.2207 0.01840 0.01035 -0.0438 0.8886 0.0541
-4.000 -0.1947 0.01752 0.00942 -0.0432 0.8798 0.0557
-3.750 -0.1693 0.01677 0.00861 -0.0425 0.8718 0.0578
-3.500 -0.1470 0.01615 0.00795 -0.0414 0.8631 0.0613
-3.250 -0.1270 0.01531 0.00714 -0.0399 0.8554 0.0659
-3.000 -0.1067 0.01485 0.00665 -0.0385 0.8469 0.0708
-2.750 -0.0865 0.01428 0.00603 -0.0370 0.8399 0.0786
-2.500 -0.0650 0.01394 0.00562 -0.0358 0.8323 0.0891
-2.250 -0.0457 0.01327 0.00509 -0.0342 0.8252 0.1322
-2.000 -0.0537 0.01140 0.00516 -0.0275 0.8175 0.6343
-1.750 -0.0345 0.01150 0.00539 -0.0250 0.8109 0.6956
-1.500 -0.0104 0.01161 0.00546 -0.0236 0.8057 0.7251
-1.250 0.0123 0.01171 0.00563 -0.0222 0.7983 0.7473
-1.000 0.0370 0.01178 0.00570 -0.0211 0.7928 0.7674
-0.750 0.0614 0.01189 0.00581 -0.0200 0.7873 0.7857
-0.500 0.0852 0.01197 0.00592 -0.0188 0.7807 0.8027
-0.250 0.1122 0.01200 0.00594 -0.0183 0.7757 0.8150
0.000 0.1378 0.01205 0.00597 -0.0180 0.7699 0.8236
0.250 0.1646 0.01206 0.00598 -0.0177 0.7636 0.8318
0.500 0.1929 0.01205 0.00591 -0.0177 0.7584 0.8401
0.750 0.2179 0.01209 0.00599 -0.0172 0.7507 0.8500
1.000 0.2463 0.01208 0.00597 -0.0171 0.7445 0.8593
1.250 0.2728 0.01212 0.00603 -0.0168 0.7378 0.8706
1.500 0.3013 0.01215 0.00609 -0.0168 0.7310 0.8815
1.750 0.3328 0.01219 0.00610 -0.0174 0.7251 0.8922
2.000 0.3623 0.01216 0.00611 -0.0175 0.7146 0.9046
2.250 0.3936 0.01211 0.00604 -0.0179 0.7038 0.9175
2.500 0.4325 0.01209 0.00600 -0.0199 0.6952 0.9262
2.750 0.4687 0.01217 0.00614 -0.0217 0.6864 0.9369
3.000 0.5073 0.01219 0.00614 -0.0237 0.6790 0.9475
3.250 0.5500 0.01224 0.00627 -0.0269 0.6691 0.9541
3.500 0.5899 0.01225 0.00627 -0.0294 0.6602 0.9634
3.750 0.6337 0.01220 0.00627 -0.0327 0.6492 0.9703
4.000 0.6756 0.01217 0.00630 -0.0358 0.6370 0.9789
4.250 0.7181 0.01208 0.00627 -0.0389 0.6232 0.9874
4.500 0.7619 0.01196 0.00619 -0.0424 0.6066 0.9954
4.750 0.7946 0.01182 0.00607 -0.0437 0.5882 1.0000
5.000 0.8093 0.01178 0.00601 -0.0414 0.5703 1.0000
5.250 0.8245 0.01179 0.00605 -0.0391 0.5476 1.0000
5.500 0.8398 0.01187 0.00608 -0.0367 0.5194 1.0000
5.750 0.8532 0.01206 0.00613 -0.0339 0.4770 1.0000
6.000 0.8626 0.01251 0.00628 -0.0305 0.4133 1.0000
6.250 0.8686 0.01325 0.00663 -0.0267 0.3497 1.0000
6.500 0.8766 0.01403 0.00712 -0.0234 0.3102 1.0000
6.750 0.8880 0.01470 0.00763 -0.0207 0.2814 1.0000
7.000 0.9016 0.01525 0.00810 -0.0184 0.2563 1.0000
7.250 0.9145 0.01583 0.00859 -0.0160 0.2354 1.0000
7.500 0.9285 0.01635 0.00908 -0.0137 0.2157 1.0000
7.750 0.9419 0.01691 0.00959 -0.0115 0.1970 1.0000
8.000 0.9543 0.01750 0.01013 -0.0091 0.1785 1.0000
8.250 0.9664 0.01811 0.01071 -0.0067 0.1565 1.0000
8.500 0.9756 0.01887 0.01135 -0.0039 0.1251 1.0000
8.750 0.9760 0.02003 0.01221 0.0002 0.0929 1.0000
9.000 0.9772 0.02114 0.01323 0.0042 0.0769 1.0000
9.250 0.9786 0.02236 0.01437 0.0078 0.0683 1.0000
9.500 0.9861 0.02338 0.01543 0.0104 0.0618 1.0000
9.750 0.9899 0.02473 0.01677 0.0131 0.0571 1.0000
10.000 0.9993 0.02581 0.01792 0.0151 0.0534 1.0000
10.250 1.0056 0.02718 0.01926 0.0172 0.0499 1.0000
10.500 1.0147 0.02861 0.02074 0.0190 0.0474 1.0000
10.750 1.0264 0.02985 0.02207 0.0205 0.0451 1.0000
11.000 1.0375 0.03114 0.02340 0.0218 0.0427 1.0000
11.250 1.0528 0.03300 0.02519 0.0229 0.0402 1.0000
11.500 1.0649 0.03437 0.02673 0.0242 0.0386 1.0000
11.750 1.0787 0.03586 0.02836 0.0253 0.0371 1.0000
12.000 1.0918 0.03749 0.03011 0.0264 0.0357 1.0000
12.250 1.1041 0.03918 0.03188 0.0274 0.0344 1.0000
12.500 1.1213 0.04127 0.03401 0.0280 0.0331 1.0000
12.750 1.1326 0.04441 0.03738 0.0289 0.0321 1.0000
13.000 1.1264 0.04629 0.03952 0.0307 0.0313 1.0000
13.250 1.1262 0.04885 0.04233 0.0320 0.0309 1.0000
13.500 1.1223 0.05172 0.04545 0.0331 0.0306 1.0000
13.750 1.1155 0.05497 0.04895 0.0339 0.0304 1.0000
14.000 1.1051 0.05856 0.05279 0.0344 0.0302 1.0000
14.250 1.0918 0.06258 0.05706 0.0345 0.0301 1.0000
14.500 1.0761 0.06692 0.06163 0.0341 0.0300 1.0000
14.750 1.0576 0.07184 0.06679 0.0330 0.0299 1.0000
15.000 1.0358 0.07757 0.07275 0.0312 0.0301 1.0000
15.250 1.0132 0.08383 0.07922 0.0286 0.0303 1.0000
15.500 0.9881 0.09105 0.08663 0.0250 0.0306 1.0000
15.750 0.9627 0.09905 0.09481 0.0206 0.0311 1.0000
16.000 0.9293 0.10948 0.10542 0.0141 0.0312 1.0000
16.250 0.9025 0.11955 0.11561 0.0080 0.0318 1.0000
16.500 0.8750 0.13064 0.12676 0.0019 0.0324 1.0000
|
Polar data table (+)
Polar graphs
<< Back to KC-135 BL124.32 AIRFOIL (kc135b-il)