KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 500,000 Max Cl/Cd: 73.18 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135a-il-500000-n5.txt Download as CSV file: xf-kc135a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL52.44 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8556 0.08467 0.08146 -0.0444 1.0000 0.0129
-16.250 -0.8844 0.07590 0.07248 -0.0495 1.0000 0.0130
-16.000 -0.9280 0.06581 0.06204 -0.0546 1.0000 0.0128
-15.750 -0.9356 0.06170 0.05783 -0.0564 1.0000 0.0130
-15.500 -0.9451 0.05757 0.05357 -0.0579 1.0000 0.0130
-15.250 -0.9437 0.05502 0.05096 -0.0588 1.0000 0.0132
-15.000 -0.9622 0.05004 0.04572 -0.0599 1.0000 0.0131
-14.750 -0.9635 0.04735 0.04294 -0.0603 1.0000 0.0132
-14.500 -0.9650 0.04467 0.04013 -0.0605 1.0000 0.0133
-14.250 -0.9651 0.04223 0.03757 -0.0605 1.0000 0.0134
-14.000 -0.9625 0.04017 0.03541 -0.0603 1.0000 0.0136
-13.750 -0.9623 0.03784 0.03293 -0.0597 1.0000 0.0137
-13.500 -0.9581 0.03602 0.03099 -0.0591 1.0000 0.0138
-13.250 -0.9531 0.03433 0.02919 -0.0582 1.0000 0.0140
-13.000 -0.9483 0.03259 0.02732 -0.0571 1.0000 0.0140
-12.750 -0.9419 0.03108 0.02567 -0.0559 1.0000 0.0142
-12.500 -0.9350 0.02961 0.02409 -0.0545 1.0000 0.0143
-12.250 -0.9267 0.02834 0.02271 -0.0531 1.0000 0.0144
-12.000 -0.9179 0.02715 0.02140 -0.0514 1.0000 0.0146
-11.750 -0.9085 0.02606 0.02022 -0.0497 1.0000 0.0148
-11.500 -0.8989 0.02507 0.01913 -0.0478 1.0000 0.0149
-11.250 -0.8893 0.02415 0.01812 -0.0457 1.0000 0.0150
-11.000 -0.8801 0.02328 0.01717 -0.0434 1.0000 0.0151
-10.750 -0.8727 0.02244 0.01629 -0.0408 1.0000 0.0153
-10.500 -0.8663 0.02171 0.01554 -0.0377 1.0000 0.0155
-10.250 -0.8404 0.02087 0.01467 -0.0384 0.9843 0.0157
-10.000 -0.8038 0.02000 0.01375 -0.0412 0.9656 0.0160
-9.750 -0.7578 0.01908 0.01275 -0.0460 0.9434 0.0165
-9.500 -0.7117 0.01819 0.01176 -0.0507 0.9114 0.0170
-9.250 -0.6863 0.01760 0.01097 -0.0509 0.8694 0.0174
-9.000 -0.6723 0.01720 0.01038 -0.0486 0.8349 0.0178
-8.750 -0.6588 0.01689 0.00991 -0.0461 0.8092 0.0182
-8.500 -0.6449 0.01646 0.00939 -0.0438 0.7902 0.0186
-8.250 -0.6275 0.01612 0.00898 -0.0420 0.7751 0.0192
-8.000 -0.6100 0.01575 0.00852 -0.0403 0.7623 0.0196
-7.750 -0.5914 0.01541 0.00809 -0.0388 0.7514 0.0202
-7.500 -0.5723 0.01505 0.00766 -0.0373 0.7411 0.0210
-7.250 -0.5522 0.01473 0.00724 -0.0360 0.7328 0.0217
-7.000 -0.5323 0.01436 0.00685 -0.0346 0.7247 0.0226
-6.750 -0.5109 0.01408 0.00652 -0.0335 0.7176 0.0236
-6.500 -0.4889 0.01380 0.00618 -0.0325 0.7104 0.0247
-6.250 -0.4669 0.01353 0.00585 -0.0315 0.7035 0.0259
-6.000 -0.4445 0.01324 0.00555 -0.0306 0.6970 0.0273
-5.750 -0.4213 0.01301 0.00527 -0.0298 0.6902 0.0289
-5.250 -0.3743 0.01254 0.00474 -0.0282 0.6789 0.0325
-5.000 -0.3500 0.01235 0.00451 -0.0276 0.6733 0.0347
-4.750 -0.3261 0.01214 0.00427 -0.0269 0.6681 0.0371
-4.500 -0.3014 0.01194 0.00406 -0.0263 0.6631 0.0401
-4.250 -0.2766 0.01174 0.00385 -0.0258 0.6578 0.0434
-4.000 -0.2519 0.01156 0.00365 -0.0252 0.6524 0.0476
-3.750 -0.2271 0.01138 0.00345 -0.0246 0.6473 0.0529
-3.500 -0.2019 0.01118 0.00327 -0.0242 0.6420 0.0605
-3.250 -0.1774 0.01095 0.00308 -0.0236 0.6369 0.0766
-3.000 -0.1555 0.01052 0.00284 -0.0226 0.6324 0.1326
-2.750 -0.1499 0.00880 0.00225 -0.0192 0.6280 0.4217
-2.500 -0.1262 0.00856 0.00219 -0.0184 0.6230 0.4760
-2.250 -0.1005 0.00848 0.00215 -0.0180 0.6181 0.5050
-2.000 -0.0746 0.00843 0.00213 -0.0175 0.6134 0.5280
-1.750 -0.0478 0.00839 0.00212 -0.0172 0.6082 0.5450
-1.500 -0.0205 0.00839 0.00210 -0.0171 0.6033 0.5573
-1.250 0.0062 0.00839 0.00208 -0.0168 0.5989 0.5685
-1.000 0.0334 0.00837 0.00208 -0.0166 0.5942 0.5793
-0.750 0.0609 0.00837 0.00207 -0.0164 0.5890 0.5872
-0.500 0.0885 0.00840 0.00204 -0.0164 0.5838 0.5918
-0.250 0.1160 0.00839 0.00202 -0.0162 0.5787 0.5958
0.000 0.1436 0.00838 0.00201 -0.0162 0.5732 0.5999
0.250 0.1711 0.00840 0.00201 -0.0161 0.5680 0.6041
0.500 0.1988 0.00844 0.00200 -0.0160 0.5634 0.6081
0.750 0.2264 0.00843 0.00202 -0.0160 0.5583 0.6122
1.000 0.2534 0.00845 0.00202 -0.0158 0.5512 0.6168
1.250 0.2805 0.00848 0.00203 -0.0156 0.5421 0.6216
1.500 0.3073 0.00853 0.00204 -0.0154 0.5330 0.6261
1.750 0.3345 0.00854 0.00207 -0.0153 0.5265 0.6306
2.000 0.3614 0.00856 0.00211 -0.0151 0.5197 0.6359
2.250 0.3883 0.00862 0.00216 -0.0149 0.5138 0.6415
2.500 0.4155 0.00864 0.00221 -0.0148 0.5073 0.6470
2.750 0.4420 0.00868 0.00227 -0.0145 0.5004 0.6528
3.000 0.4689 0.00872 0.00233 -0.0144 0.4935 0.6593
3.250 0.4952 0.00877 0.00240 -0.0141 0.4857 0.6661
3.500 0.5214 0.00881 0.00248 -0.0138 0.4774 0.6739
3.750 0.5474 0.00888 0.00256 -0.0134 0.4678 0.6819
4.000 0.5731 0.00893 0.00265 -0.0131 0.4568 0.6910
4.250 0.5982 0.00901 0.00275 -0.0126 0.4441 0.7011
4.500 0.6226 0.00910 0.00286 -0.0120 0.4280 0.7133
4.750 0.6460 0.00922 0.00299 -0.0111 0.4067 0.7266
5.000 0.6676 0.00942 0.00315 -0.0101 0.3799 0.7416
5.250 0.6878 0.00969 0.00336 -0.0087 0.3512 0.7594
5.500 0.7075 0.00996 0.00361 -0.0073 0.3248 0.7819
5.750 0.7270 0.01021 0.00388 -0.0058 0.3008 0.8090
6.000 0.7461 0.01047 0.00417 -0.0043 0.2775 0.8416
6.250 0.7679 0.01075 0.00448 -0.0033 0.2581 0.8783
6.500 0.7987 0.01108 0.00485 -0.0042 0.2406 0.9139
6.750 0.8386 0.01152 0.00527 -0.0073 0.2224 0.9399
7.000 0.8774 0.01199 0.00569 -0.0102 0.2043 0.9578
7.250 0.9115 0.01255 0.00614 -0.0123 0.1816 0.9704
7.500 0.9433 0.01305 0.00655 -0.0138 0.1627 0.9803
7.750 0.9734 0.01351 0.00696 -0.0149 0.1492 0.9894
8.000 1.0012 0.01399 0.00739 -0.0156 0.1376 0.9985
8.250 1.0217 0.01435 0.00774 -0.0147 0.1286 1.0000
8.500 1.0341 0.01473 0.00810 -0.0121 0.1208 1.0000
8.750 1.0454 0.01515 0.00849 -0.0093 0.1121 1.0000
9.000 1.0546 0.01553 0.00886 -0.0062 0.1047 1.0000
9.250 1.0609 0.01598 0.00927 -0.0025 0.0973 1.0000
9.500 1.0697 0.01643 0.00972 0.0005 0.0904 1.0000
9.750 1.0785 0.01697 0.01025 0.0033 0.0834 1.0000
10.250 1.0969 0.01826 0.01151 0.0082 0.0691 1.0000
10.500 1.1055 0.01904 0.01228 0.0104 0.0614 1.0000
10.750 1.1138 0.01993 0.01315 0.0125 0.0544 1.0000
11.000 1.1217 0.02091 0.01412 0.0143 0.0477 1.0000
11.250 1.1293 0.02201 0.01520 0.0160 0.0419 1.0000
11.500 1.1382 0.02309 0.01630 0.0174 0.0382 1.0000
11.750 1.1471 0.02425 0.01749 0.0186 0.0353 1.0000
12.000 1.1554 0.02552 0.01878 0.0198 0.0326 1.0000
12.250 1.1637 0.02684 0.02013 0.0208 0.0305 1.0000
12.500 1.1728 0.02815 0.02149 0.0216 0.0289 1.0000
12.750 1.1801 0.02964 0.02301 0.0224 0.0274 1.0000
13.000 1.1874 0.03117 0.02460 0.0231 0.0265 1.0000
13.250 1.1956 0.03267 0.02617 0.0237 0.0255 1.0000
13.500 1.2028 0.03426 0.02782 0.0242 0.0246 1.0000
13.750 1.2089 0.03600 0.02962 0.0247 0.0239 1.0000
14.000 1.2133 0.03793 0.03160 0.0251 0.0230 1.0000
14.250 1.2165 0.03999 0.03372 0.0255 0.0225 1.0000
14.500 1.2208 0.04202 0.03583 0.0257 0.0221 1.0000
14.750 1.2264 0.04397 0.03786 0.0258 0.0213 1.0000
15.000 1.2296 0.04620 0.04017 0.0259 0.0208 1.0000
15.250 1.2322 0.04857 0.04261 0.0258 0.0202 1.0000
15.500 1.2339 0.05110 0.04520 0.0257 0.0197 1.0000
15.750 1.2343 0.05382 0.04800 0.0254 0.0193 1.0000
16.000 1.2318 0.05696 0.05121 0.0249 0.0190 1.0000
16.250 1.2315 0.05993 0.05426 0.0244 0.0186 1.0000
16.500 1.2310 0.06298 0.05741 0.0238 0.0183 1.0000
16.750 1.2308 0.06605 0.06058 0.0231 0.0179 1.0000
17.000 1.2301 0.06923 0.06385 0.0223 0.0174 1.0000
17.250 1.2268 0.07282 0.06753 0.0213 0.0171 1.0000
17.500 1.2228 0.07658 0.07138 0.0202 0.0168 1.0000
17.750 1.2175 0.08059 0.07548 0.0189 0.0165 1.0000
18.000 1.2109 0.08484 0.07982 0.0175 0.0163 1.0000
18.250 1.2034 0.08934 0.08441 0.0158 0.0161 1.0000
18.500 1.1938 0.09422 0.08940 0.0140 0.0161 1.0000
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