KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 500,000 Max Cl/Cd: 89.17 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135b-il-500000.txt Download as CSV file: xf-kc135b-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4544 0.07080 0.06846 -0.0519 1.0000 0.0249
-10.250 -0.5100 0.05899 0.05651 -0.0554 1.0000 0.0251
-10.000 -0.5344 0.05501 0.05244 -0.0549 1.0000 0.0251
-9.750 -0.5581 0.05123 0.04859 -0.0529 1.0000 0.0252
-9.500 -0.5641 0.04813 0.04552 -0.0510 1.0000 0.0255
-9.250 -0.5773 0.04573 0.04309 -0.0476 1.0000 0.0256
-9.000 -0.5875 0.04307 0.04038 -0.0444 1.0000 0.0257
-8.750 -0.5881 0.04036 0.03763 -0.0429 0.9976 0.0259
-8.500 -0.5722 0.03672 0.03388 -0.0448 0.9866 0.0265
-8.250 -0.5541 0.03287 0.02987 -0.0468 0.9753 0.0273
-8.000 -0.5353 0.02891 0.02568 -0.0482 0.9595 0.0287
-7.750 -0.5133 0.02705 0.02322 -0.0474 0.9350 0.0309
-7.500 -0.5158 0.02050 0.01625 -0.0453 0.9103 0.0317
-7.250 -0.4999 0.01823 0.01390 -0.0446 0.8912 0.0322
-7.000 -0.4842 0.01654 0.01208 -0.0434 0.8743 0.0328
-6.750 -0.4676 0.01507 0.01045 -0.0422 0.8599 0.0337
-6.500 -0.4496 0.01388 0.00908 -0.0409 0.8474 0.0357
-6.250 -0.4407 0.02026 0.01406 -0.0397 0.8651 0.0254
-6.000 -0.4160 0.01888 0.01248 -0.0390 0.8524 0.0253
-5.750 -0.3910 0.01736 0.01082 -0.0385 0.8411 0.0256
-5.500 -0.3666 0.01657 0.00997 -0.0380 0.8308 0.0265
-5.250 -0.3418 0.01586 0.00917 -0.0375 0.8218 0.0271
-5.000 -0.3171 0.01505 0.00829 -0.0368 0.8128 0.0277
-4.750 -0.2929 0.01437 0.00752 -0.0361 0.8053 0.0285
-4.500 -0.2693 0.01375 0.00684 -0.0353 0.7973 0.0294
-4.250 -0.2459 0.01328 0.00627 -0.0344 0.7904 0.0303
-4.000 -0.2238 0.01268 0.00562 -0.0333 0.7832 0.0314
-3.750 -0.2032 0.01206 0.00497 -0.0320 0.7767 0.0334
-3.500 -0.1789 0.01181 0.00471 -0.0314 0.7707 0.0359
-3.250 -0.1546 0.01155 0.00440 -0.0307 0.7642 0.0382
-3.000 -0.1328 0.01106 0.00383 -0.0296 0.7586 0.0413
-2.750 -0.1082 0.01080 0.00358 -0.0290 0.7528 0.0453
-2.500 -0.0832 0.01058 0.00332 -0.0284 0.7471 0.0499
-2.250 -0.0586 0.01033 0.00302 -0.0278 0.7420 0.0571
-2.000 -0.0337 0.01007 0.00279 -0.0272 0.7364 0.0687
-1.750 -0.0232 0.00846 0.00224 -0.0247 0.7310 0.3845
-1.500 -0.0090 0.00773 0.00226 -0.0221 0.7263 0.6074
-1.250 0.0160 0.00769 0.00229 -0.0214 0.7209 0.6404
-1.000 0.0420 0.00768 0.00229 -0.0209 0.7154 0.6612
-0.750 0.0687 0.00772 0.00228 -0.0206 0.7103 0.6764
-0.500 0.0950 0.00768 0.00229 -0.0202 0.7044 0.6894
-0.250 0.1217 0.00765 0.00228 -0.0199 0.6988 0.7012
0.000 0.1483 0.00768 0.00229 -0.0195 0.6937 0.7149
0.250 0.1748 0.00765 0.00229 -0.0192 0.6877 0.7269
0.500 0.2019 0.00763 0.00229 -0.0190 0.6825 0.7362
0.750 0.2294 0.00764 0.00228 -0.0189 0.6772 0.7433
1.000 0.2561 0.00758 0.00226 -0.0187 0.6692 0.7508
1.250 0.2830 0.00756 0.00221 -0.0184 0.6608 0.7585
1.500 0.3095 0.00750 0.00219 -0.0181 0.6519 0.7672
1.750 0.3363 0.00749 0.00219 -0.0179 0.6450 0.7768
2.000 0.3629 0.00746 0.00221 -0.0176 0.6372 0.7882
2.250 0.3895 0.00745 0.00223 -0.0174 0.6310 0.8004
2.500 0.4159 0.00741 0.00229 -0.0170 0.6236 0.8147
2.750 0.4420 0.00740 0.00232 -0.0166 0.6165 0.8319
3.000 0.4681 0.00736 0.00239 -0.0162 0.6079 0.8524
3.250 0.4949 0.00737 0.00247 -0.0159 0.6005 0.8748
3.500 0.5230 0.00737 0.00257 -0.0159 0.5909 0.8991
3.750 0.5546 0.00742 0.00268 -0.0166 0.5803 0.9206
4.000 0.5895 0.00752 0.00280 -0.0182 0.5687 0.9378
4.250 0.6252 0.00763 0.00292 -0.0199 0.5532 0.9513
4.500 0.6599 0.00776 0.00305 -0.0214 0.5344 0.9629
4.750 0.6979 0.00795 0.00319 -0.0238 0.5095 0.9692
5.000 0.7321 0.00821 0.00336 -0.0254 0.4739 0.9768
5.250 0.7633 0.00882 0.00363 -0.0266 0.3947 0.9846
5.500 0.7947 0.00975 0.00411 -0.0283 0.3109 0.9908
5.750 0.8291 0.01033 0.00449 -0.0304 0.2675 0.9961
6.000 0.8648 0.01082 0.00483 -0.0328 0.2333 1.0000
6.250 0.8799 0.01115 0.00509 -0.0306 0.2135 1.0000
6.500 0.8954 0.01150 0.00537 -0.0285 0.1964 1.0000
6.750 0.9114 0.01186 0.00567 -0.0265 0.1810 1.0000
7.000 0.9276 0.01221 0.00598 -0.0245 0.1664 1.0000
7.250 0.9441 0.01257 0.00629 -0.0226 0.1519 1.0000
7.500 0.9603 0.01296 0.00663 -0.0206 0.1358 1.0000
7.750 0.9752 0.01343 0.00700 -0.0185 0.1141 1.0000
8.000 0.9850 0.01418 0.00752 -0.0156 0.0809 1.0000
8.250 0.9933 0.01500 0.00818 -0.0124 0.0552 1.0000
8.500 1.0041 0.01568 0.00879 -0.0096 0.0449 1.0000
8.750 1.0143 0.01638 0.00947 -0.0067 0.0394 1.0000
9.000 1.0267 0.01689 0.01002 -0.0042 0.0366 1.0000
9.250 1.0341 0.01752 0.01066 -0.0009 0.0339 1.0000
9.500 1.0401 0.01829 0.01148 0.0025 0.0319 1.0000
9.750 1.0517 0.01888 0.01213 0.0048 0.0303 1.0000
10.000 1.0622 0.01958 0.01288 0.0071 0.0289 1.0000
10.250 1.0699 0.02049 0.01382 0.0096 0.0274 1.0000
10.500 1.0700 0.02194 0.01533 0.0127 0.0259 1.0000
10.750 1.0834 0.02266 0.01613 0.0142 0.0251 1.0000
11.000 1.0951 0.02351 0.01705 0.0157 0.0238 1.0000
11.250 1.1043 0.02459 0.01818 0.0172 0.0228 1.0000
11.500 1.1114 0.02587 0.01950 0.0188 0.0219 1.0000
11.750 1.1115 0.02777 0.02145 0.0208 0.0209 1.0000
12.000 1.1181 0.02926 0.02305 0.0222 0.0203 1.0000
12.250 1.1279 0.03052 0.02440 0.0232 0.0196 1.0000
12.500 1.1351 0.03203 0.02599 0.0243 0.0192 1.0000
12.750 1.1418 0.03363 0.02768 0.0253 0.0187 1.0000
13.000 1.1493 0.03515 0.02925 0.0259 0.0177 1.0000
13.250 1.1549 0.03690 0.03106 0.0267 0.0174 1.0000
13.500 1.1580 0.03894 0.03316 0.0276 0.0170 1.0000
13.750 1.1562 0.04159 0.03587 0.0289 0.0164 1.0000
14.000 1.1617 0.04344 0.03787 0.0292 0.0161 1.0000
14.250 1.1654 0.04557 0.04013 0.0296 0.0158 1.0000
14.500 1.1674 0.04793 0.04261 0.0300 0.0155 1.0000
14.750 1.1696 0.05027 0.04507 0.0300 0.0150 1.0000
15.000 1.1704 0.05288 0.04779 0.0300 0.0148 1.0000
15.250 1.1702 0.05568 0.05071 0.0298 0.0146 1.0000
15.500 1.1680 0.05879 0.05394 0.0296 0.0144 1.0000
15.750 1.1653 0.06208 0.05737 0.0292 0.0144 1.0000
16.000 1.1636 0.06533 0.06068 0.0281 0.0139 1.0000
16.250 1.1595 0.06901 0.06450 0.0272 0.0138 1.0000
16.500 1.1535 0.07306 0.06867 0.0261 0.0137 1.0000
16.750 1.1477 0.07723 0.07295 0.0246 0.0135 1.0000
17.000 1.1413 0.08160 0.07744 0.0229 0.0134 1.0000
17.250 1.1322 0.08640 0.08232 0.0211 0.0132 1.0000
17.500 1.1202 0.09213 0.08825 0.0185 0.0133 1.0000
17.750 1.1075 0.09796 0.09420 0.0158 0.0131 1.0000
18.000 1.0933 0.10444 0.10084 0.0124 0.0132 1.0000
18.250 1.0763 0.11180 0.10837 0.0083 0.0132 1.0000
18.500 1.0578 0.11951 0.11622 0.0041 0.0131 1.0000
18.750 1.0382 0.12799 0.12487 -0.0010 0.0131 1.0000
19.000 1.0198 0.13658 0.13362 -0.0062 0.0132 1.0000
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