KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 200,000 Max Cl/Cd: 74.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135d-il-200000.txt Download as CSV file: xf-kc135d-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL351.6 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4386 0.08674 0.08326 -0.0295 1.0000 0.0268
-8.250 -0.4401 0.08316 0.07973 -0.0315 1.0000 0.0270
-8.000 -0.4453 0.07950 0.07613 -0.0337 1.0000 0.0276
-7.750 -0.4531 0.07593 0.07260 -0.0357 1.0000 0.0276
-7.500 -0.4563 0.07241 0.06908 -0.0369 1.0000 0.0279
-7.250 -0.4585 0.06912 0.06576 -0.0373 1.0000 0.0284
-7.000 -0.4602 0.06600 0.06262 -0.0370 1.0000 0.0290
-6.750 -0.4624 0.06319 0.05975 -0.0358 1.0000 0.0300
-6.500 -0.4644 0.06160 0.05802 -0.0334 1.0000 0.0316
-6.250 -0.4679 0.06124 0.05745 -0.0298 1.0000 0.0324
-6.000 -0.4707 0.06051 0.05653 -0.0262 1.0000 0.0327
-5.750 -0.4579 0.05335 0.04917 -0.0286 0.9962 0.0336
-5.500 -0.4350 0.04815 0.04400 -0.0317 0.9917 0.0350
-5.250 -0.4069 0.04442 0.04011 -0.0346 0.9865 0.0370
-5.000 -0.3752 0.04111 0.03655 -0.0373 0.9817 0.0399
-4.750 -0.3342 0.04172 0.03646 -0.0381 0.9746 0.0455
-4.500 -0.3091 0.03482 0.02944 -0.0410 0.9709 0.0480
-4.250 -0.2823 0.03212 0.02667 -0.0424 0.9646 0.0517
-4.000 -0.2477 0.03028 0.02425 -0.0436 0.9594 0.0614
-3.750 -0.1746 0.01182 0.00581 -0.0508 0.9447 0.0889
-3.500 -0.1464 0.00893 0.00302 -0.0529 0.9421 0.1073
-2.750 -0.0939 0.01994 0.01333 -0.0512 0.9350 0.1798
-2.500 -0.0371 0.01837 0.01076 -0.0499 0.9325 0.0576
-2.250 0.0002 0.01652 0.00880 -0.0511 0.9293 0.0525
-2.000 0.0303 0.01549 0.00770 -0.0511 0.9231 0.0517
-1.750 0.0607 0.01473 0.00692 -0.0515 0.9171 0.0553
-1.500 0.0913 0.01401 0.00618 -0.0518 0.9120 0.0575
-1.250 0.1157 0.01354 0.00568 -0.0510 0.9038 0.0592
-1.000 0.1437 0.01288 0.00498 -0.0509 0.8986 0.0648
-0.750 0.1674 0.01265 0.00469 -0.0501 0.8899 0.0757
-0.500 0.1826 0.01093 0.00435 -0.0481 0.8829 0.5065
-0.250 0.2356 0.00996 0.00481 -0.0504 0.8810 0.9536
0.000 0.3105 0.01004 0.00475 -0.0595 0.8787 0.9825
0.250 0.3808 0.00983 0.00443 -0.0680 0.8728 0.9990
0.500 0.3997 0.00970 0.00421 -0.0664 0.8588 1.0000
0.750 0.4165 0.00961 0.00404 -0.0642 0.8452 1.0000
1.000 0.4351 0.00959 0.00397 -0.0625 0.8334 1.0000
1.250 0.4554 0.00960 0.00393 -0.0610 0.8231 1.0000
1.500 0.4767 0.00960 0.00386 -0.0595 0.8128 1.0000
1.750 0.4978 0.00962 0.00385 -0.0581 0.8017 1.0000
2.000 0.5194 0.00968 0.00391 -0.0569 0.7911 1.0000
2.250 0.5419 0.00972 0.00394 -0.0557 0.7809 1.0000
2.500 0.5650 0.00975 0.00395 -0.0546 0.7705 1.0000
2.750 0.5877 0.00980 0.00400 -0.0534 0.7590 1.0000
3.000 0.6103 0.00985 0.00406 -0.0522 0.7465 1.0000
3.250 0.6331 0.00989 0.00415 -0.0511 0.7333 1.0000
3.500 0.6561 0.00994 0.00421 -0.0499 0.7191 1.0000
3.750 0.6790 0.00997 0.00427 -0.0486 0.7032 1.0000
4.000 0.7017 0.01002 0.00433 -0.0474 0.6852 1.0000
4.250 0.7238 0.01006 0.00444 -0.0460 0.6626 1.0000
4.500 0.7455 0.01012 0.00451 -0.0445 0.6345 1.0000
4.750 0.7648 0.01024 0.00452 -0.0424 0.5852 1.0000
5.000 0.7790 0.01069 0.00454 -0.0394 0.4861 1.0000
5.250 0.7896 0.01163 0.00489 -0.0363 0.3810 1.0000
5.500 0.8046 0.01244 0.00540 -0.0342 0.3189 1.0000
5.750 0.8218 0.01316 0.00593 -0.0325 0.2746 1.0000
6.000 0.8401 0.01381 0.00643 -0.0310 0.2334 1.0000
6.250 0.8554 0.01475 0.00701 -0.0292 0.1547 1.0000
6.500 0.8620 0.01676 0.00829 -0.0260 0.0592 1.0000
6.750 0.8773 0.01791 0.00944 -0.0239 0.0477 1.0000
7.000 0.8906 0.01923 0.01080 -0.0216 0.0410 1.0000
7.250 0.9073 0.02030 0.01197 -0.0198 0.0377 1.0000
7.500 0.9237 0.02157 0.01328 -0.0180 0.0350 1.0000
7.750 0.9409 0.02322 0.01495 -0.0164 0.0330 1.0000
8.000 0.9618 0.02571 0.01751 -0.0155 0.0308 1.0000
8.250 0.9832 0.02701 0.01905 -0.0144 0.0292 1.0000
8.500 1.0055 0.02912 0.02139 -0.0135 0.0286 1.0000
8.750 1.0259 0.03162 0.02419 -0.0123 0.0282 1.0000
9.000 1.0429 0.03456 0.02749 -0.0107 0.0283 1.0000
9.250 1.0552 0.03799 0.03133 -0.0087 0.0290 1.0000
9.500 1.0623 0.04204 0.03578 -0.0064 0.0299 1.0000
9.750 1.0643 0.04673 0.04082 -0.0040 0.0307 1.0000
10.000 1.0741 0.05108 0.04538 -0.0025 0.0318 1.0000
16.500 0.6758 0.18304 0.17990 -0.0437 0.0418 1.0000
16.750 0.6730 0.18634 0.18320 -0.0467 0.0416 1.0000
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Polar data table (+)
Polar graphs
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