KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 100,000 Max Cl/Cd: 49.25 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135b-il-100000-n5.txt Download as CSV file: xf-kc135b-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4262 0.07887 0.07394 -0.0471 1.0000 0.0382
-10.000 -0.5412 0.07691 0.07160 -0.0503 1.0000 0.0378
-9.750 -0.5497 0.07330 0.06800 -0.0505 1.0000 0.0372
-9.500 -0.5647 0.06991 0.06457 -0.0499 1.0000 0.0367
-9.250 -0.5811 0.06701 0.06161 -0.0476 1.0000 0.0361
-9.000 -0.5940 0.06404 0.05856 -0.0453 1.0000 0.0356
-8.750 -0.6050 0.06099 0.05540 -0.0426 1.0000 0.0349
-8.500 -0.6143 0.05800 0.05225 -0.0396 1.0000 0.0343
-8.250 -0.6222 0.05505 0.04913 -0.0363 1.0000 0.0337
-8.000 -0.6295 0.05229 0.04617 -0.0324 1.0000 0.0332
-7.750 -0.6378 0.04989 0.04355 -0.0280 1.0000 0.0327
-7.500 -0.6171 0.04652 0.03985 -0.0293 0.9893 0.0332
-7.250 -0.5926 0.04364 0.03665 -0.0308 0.9784 0.0345
-7.000 -0.5678 0.04058 0.03319 -0.0317 0.9678 0.0350
-6.750 -0.5414 0.03755 0.02973 -0.0326 0.9582 0.0350
-6.500 -0.5119 0.03479 0.02656 -0.0336 0.9500 0.0351
-6.250 -0.4841 0.03248 0.02387 -0.0340 0.9399 0.0354
-6.000 -0.4515 0.03030 0.02132 -0.0351 0.9328 0.0359
-5.750 -0.4221 0.02866 0.01933 -0.0354 0.9228 0.0376
-5.500 -0.3892 0.02707 0.01741 -0.0363 0.9152 0.0392
-5.250 -0.3583 0.02544 0.01572 -0.0372 0.9065 0.0403
-5.000 -0.3257 0.02410 0.01431 -0.0381 0.8989 0.0417
-4.750 -0.2956 0.02301 0.01314 -0.0385 0.8901 0.0436
-4.500 -0.2660 0.02216 0.01219 -0.0388 0.8820 0.0469
-4.250 -0.2385 0.02122 0.01120 -0.0387 0.8734 0.0492
-4.000 -0.2152 0.02029 0.01033 -0.0380 0.8647 0.0516
-3.750 -0.1916 0.01966 0.00967 -0.0373 0.8565 0.0558
-3.500 -0.1690 0.01920 0.00908 -0.0363 0.8479 0.0602
-3.250 -0.1481 0.01852 0.00836 -0.0352 0.8401 0.0649
-3.000 -0.1259 0.01813 0.00785 -0.0342 0.8320 0.0726
-2.750 -0.1032 0.01762 0.00728 -0.0332 0.8248 0.0826
-2.500 -0.0815 0.01711 0.00681 -0.0322 0.8175 0.1066
-2.250 -0.0823 0.01489 0.00657 -0.0276 0.8097 0.5509
-2.000 -0.0635 0.01488 0.00672 -0.0251 0.8033 0.6463
-1.750 -0.0429 0.01495 0.00685 -0.0230 0.7961 0.6920
-1.500 -0.0185 0.01501 0.00695 -0.0215 0.7909 0.7264
-1.250 0.0031 0.01515 0.00711 -0.0197 0.7840 0.7568
-1.000 0.0289 0.01525 0.00722 -0.0186 0.7781 0.7784
-0.750 0.0561 0.01524 0.00711 -0.0183 0.7730 0.7892
-0.500 0.0832 0.01527 0.00711 -0.0182 0.7662 0.7958
-0.250 0.1105 0.01526 0.00701 -0.0182 0.7608 0.8046
0.000 0.1398 0.01529 0.00701 -0.0184 0.7554 0.8116
0.250 0.1659 0.01534 0.00704 -0.0182 0.7490 0.8211
0.500 0.1965 0.01537 0.00704 -0.0187 0.7441 0.8289
0.750 0.2241 0.01544 0.00711 -0.0187 0.7383 0.8390
1.000 0.2530 0.01553 0.00722 -0.0190 0.7323 0.8488
1.250 0.2843 0.01558 0.00725 -0.0196 0.7274 0.8584
1.500 0.3121 0.01568 0.00739 -0.0197 0.7199 0.8703
1.750 0.3445 0.01572 0.00744 -0.0205 0.7128 0.8809
2.000 0.3766 0.01579 0.00755 -0.0214 0.7044 0.8919
2.250 0.4096 0.01580 0.00757 -0.0223 0.6963 0.9036
2.500 0.4416 0.01587 0.00769 -0.0232 0.6864 0.9164
2.750 0.4782 0.01582 0.00765 -0.0247 0.6750 0.9262
3.000 0.5134 0.01574 0.00757 -0.0260 0.6626 0.9374
3.250 0.5472 0.01574 0.00763 -0.0273 0.6491 0.9497
3.500 0.5839 0.01578 0.00774 -0.0292 0.6370 0.9602
3.750 0.6210 0.01579 0.00784 -0.0313 0.6249 0.9706
4.000 0.6580 0.01580 0.00790 -0.0333 0.6117 0.9813
4.250 0.6954 0.01579 0.00797 -0.0355 0.5966 0.9919
4.500 0.7287 0.01581 0.00808 -0.0369 0.5794 1.0000
4.750 0.7449 0.01587 0.00817 -0.0348 0.5627 1.0000
5.000 0.7616 0.01595 0.00827 -0.0327 0.5437 1.0000
5.250 0.7784 0.01606 0.00840 -0.0306 0.5211 1.0000
5.500 0.7948 0.01621 0.00851 -0.0284 0.4931 1.0000
5.750 0.8102 0.01645 0.00868 -0.0261 0.4575 1.0000
6.000 0.8241 0.01681 0.00887 -0.0235 0.4143 1.0000
6.250 0.8358 0.01734 0.00918 -0.0207 0.3695 1.0000
6.500 0.8465 0.01800 0.00961 -0.0178 0.3335 1.0000
6.750 0.8578 0.01870 0.01015 -0.0152 0.3055 1.0000
7.000 0.8690 0.01943 0.01074 -0.0126 0.2786 1.0000
7.250 0.8800 0.02015 0.01134 -0.0100 0.2507 1.0000
7.500 0.8914 0.02086 0.01196 -0.0076 0.2246 1.0000
7.750 0.9027 0.02158 0.01260 -0.0053 0.2030 1.0000
8.000 0.9148 0.02228 0.01326 -0.0031 0.1839 1.0000
8.250 0.9262 0.02302 0.01397 -0.0008 0.1656 1.0000
8.500 0.9364 0.02381 0.01473 0.0015 0.1474 1.0000
8.750 0.9460 0.02458 0.01550 0.0040 0.1272 1.0000
9.000 0.9532 0.02550 0.01635 0.0067 0.1075 1.0000
9.250 0.9596 0.02658 0.01734 0.0093 0.0896 1.0000
9.500 0.9653 0.02780 0.01849 0.0117 0.0766 1.0000
9.750 0.9702 0.02916 0.01981 0.0141 0.0678 1.0000
10.000 0.9765 0.03049 0.02119 0.0161 0.0611 1.0000
10.250 0.9816 0.03197 0.02268 0.0180 0.0561 1.0000
10.500 0.9877 0.03343 0.02424 0.0197 0.0522 1.0000
10.750 0.9916 0.03511 0.02594 0.0214 0.0495 1.0000
11.000 0.9973 0.03677 0.02770 0.0228 0.0470 1.0000
11.250 1.0039 0.03841 0.02946 0.0241 0.0443 1.0000
11.500 1.0089 0.04020 0.03133 0.0252 0.0419 1.0000
11.750 1.0129 0.04216 0.03332 0.0262 0.0404 1.0000
12.000 1.0199 0.04406 0.03535 0.0273 0.0387 1.0000
12.250 1.0266 0.04598 0.03746 0.0281 0.0370 1.0000
12.500 1.0316 0.04803 0.03962 0.0288 0.0353 1.0000
12.750 1.0359 0.05018 0.04185 0.0294 0.0340 1.0000
13.000 1.0408 0.05243 0.04414 0.0300 0.0329 1.0000
13.250 1.0463 0.05487 0.04671 0.0306 0.0321 1.0000
13.500 1.0477 0.05763 0.04973 0.0310 0.0313 1.0000
13.750 1.0467 0.06067 0.05301 0.0311 0.0304 1.0000
14.000 1.0426 0.06401 0.05657 0.0308 0.0295 1.0000
14.250 1.0375 0.06757 0.06034 0.0304 0.0288 1.0000
14.500 1.0312 0.07135 0.06430 0.0295 0.0282 1.0000
14.750 1.0234 0.07549 0.06862 0.0284 0.0278 1.0000
15.000 1.0145 0.07994 0.07324 0.0269 0.0273 1.0000
15.250 1.0033 0.08498 0.07847 0.0249 0.0271 1.0000
15.500 0.9908 0.09047 0.08412 0.0224 0.0269 1.0000
15.750 0.9723 0.09744 0.09131 0.0188 0.0269 1.0000
16.000 0.9525 0.10510 0.09917 0.0145 0.0268 1.0000
16.250 0.9066 0.11966 0.11407 0.0053 0.0276 1.0000
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