KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 500,000 Max Cl/Cd: 88.73 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135a-il-500000.txt Download as CSV file: xf-kc135a-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5629 0.08677 0.08428 -0.0468 1.0000 0.0314
-12.250 -0.6033 0.07650 0.07391 -0.0539 1.0000 0.0314
-12.000 -0.6355 0.06967 0.06695 -0.0577 1.0000 0.0314
-11.750 -0.6592 0.06488 0.06206 -0.0594 1.0000 0.0315
-11.500 -0.6826 0.06079 0.05785 -0.0598 1.0000 0.0316
-11.250 -0.7037 0.05749 0.05442 -0.0588 1.0000 0.0316
-11.000 -0.8387 0.04513 0.04099 -0.0445 1.0000 0.0259
-10.750 -0.8305 0.04340 0.03928 -0.0428 1.0000 0.0262
-10.500 -0.8238 0.04218 0.03806 -0.0405 1.0000 0.0264
-10.250 -0.8351 0.03736 0.03293 -0.0360 1.0000 0.0236
-10.000 -0.8508 0.03265 0.02774 -0.0302 1.0000 0.0230
-9.750 -0.8361 0.03054 0.02542 -0.0291 0.9979 0.0232
-9.500 -0.8082 0.02745 0.02199 -0.0305 0.9912 0.0233
-9.250 -0.7764 0.02507 0.01935 -0.0322 0.9845 0.0234
-9.000 -0.7437 0.02329 0.01740 -0.0338 0.9751 0.0237
-8.750 -0.7065 0.02177 0.01573 -0.0363 0.9658 0.0242
-8.500 -0.6658 0.02037 0.01419 -0.0394 0.9544 0.0247
-8.250 -0.6224 0.01924 0.01289 -0.0429 0.9374 0.0255
-8.000 -0.5823 0.01779 0.01137 -0.0461 0.9129 0.0263
-7.750 -0.5546 0.01721 0.01071 -0.0464 0.8801 0.0272
-7.500 -0.5341 0.01672 0.01008 -0.0451 0.8519 0.0279
-7.250 -0.5150 0.01627 0.00949 -0.0436 0.8298 0.0289
-7.000 -0.4959 0.01584 0.00893 -0.0420 0.8125 0.0298
-6.750 -0.4799 0.01516 0.00816 -0.0399 0.7981 0.0309
-6.500 -0.4616 0.01472 0.00767 -0.0383 0.7860 0.0320
-6.250 -0.4412 0.01440 0.00728 -0.0370 0.7749 0.0337
-6.000 -0.4193 0.01414 0.00693 -0.0358 0.7653 0.0354
-5.750 -0.4026 0.01356 0.00631 -0.0339 0.7562 0.0376
-5.500 -0.3805 0.01328 0.00600 -0.0329 0.7483 0.0397
-5.250 -0.3582 0.01301 0.00565 -0.0319 0.7406 0.0421
-5.000 -0.3374 0.01263 0.00526 -0.0307 0.7337 0.0453
-4.750 -0.3137 0.01241 0.00500 -0.0299 0.7265 0.0483
-4.500 -0.2922 0.01206 0.00460 -0.0288 0.7201 0.0522
-4.250 -0.2681 0.01183 0.00435 -0.0281 0.7134 0.0566
-4.000 -0.2454 0.01150 0.00402 -0.0271 0.7068 0.0631
-3.750 -0.2221 0.01124 0.00373 -0.0262 0.7008 0.0735
-3.250 -0.2031 0.00863 0.00275 -0.0204 0.6891 0.4730
-3.000 -0.1794 0.00855 0.00275 -0.0195 0.6837 0.5243
-2.750 -0.1539 0.00851 0.00277 -0.0189 0.6780 0.5479
-2.500 -0.1274 0.00852 0.00275 -0.0185 0.6724 0.5637
-2.250 -0.1006 0.00859 0.00274 -0.0181 0.6671 0.5767
-2.000 -0.0741 0.00861 0.00276 -0.0178 0.6615 0.5898
-1.750 -0.0474 0.00860 0.00277 -0.0174 0.6561 0.6004
-1.500 -0.0202 0.00867 0.00275 -0.0172 0.6512 0.6095
-1.250 0.0069 0.00865 0.00276 -0.0170 0.6462 0.6185
-1.000 0.0338 0.00868 0.00276 -0.0167 0.6408 0.6279
-0.750 0.0611 0.00864 0.00274 -0.0165 0.6357 0.6349
-0.500 0.0889 0.00868 0.00272 -0.0165 0.6307 0.6401
-0.250 0.1166 0.00866 0.00269 -0.0164 0.6252 0.6449
0.000 0.1443 0.00861 0.00265 -0.0163 0.6200 0.6497
0.250 0.1721 0.00864 0.00264 -0.0163 0.6154 0.6549
0.500 0.1997 0.00863 0.00265 -0.0163 0.6104 0.6601
0.750 0.2274 0.00860 0.00263 -0.0162 0.6051 0.6652
1.000 0.2547 0.00860 0.00261 -0.0161 0.5990 0.6709
1.250 0.2816 0.00857 0.00260 -0.0158 0.5912 0.6771
1.500 0.3086 0.00855 0.00257 -0.0156 0.5843 0.6831
1.750 0.3357 0.00855 0.00259 -0.0155 0.5787 0.6896
2.000 0.3629 0.00855 0.00262 -0.0153 0.5726 0.6968
2.250 0.3898 0.00855 0.00264 -0.0151 0.5671 0.7042
2.500 0.4167 0.00857 0.00269 -0.0150 0.5616 0.7130
2.750 0.4434 0.00854 0.00273 -0.0147 0.5554 0.7219
3.000 0.4700 0.00858 0.00277 -0.0144 0.5496 0.7324
3.250 0.4961 0.00856 0.00284 -0.0141 0.5435 0.7443
3.500 0.5220 0.00854 0.00290 -0.0137 0.5366 0.7582
3.750 0.5475 0.00855 0.00297 -0.0132 0.5301 0.7751
4.000 0.5727 0.00851 0.00306 -0.0126 0.5223 0.7955
4.250 0.5973 0.00852 0.00314 -0.0119 0.5147 0.8212
4.500 0.6226 0.00847 0.00326 -0.0113 0.5058 0.8518
4.750 0.6497 0.00850 0.00338 -0.0110 0.4966 0.8851
5.000 0.6822 0.00856 0.00354 -0.0120 0.4850 0.9146
5.250 0.7202 0.00869 0.00371 -0.0142 0.4711 0.9359
5.500 0.7592 0.00886 0.00389 -0.0166 0.4549 0.9508
5.750 0.7962 0.00909 0.00407 -0.0188 0.4336 0.9622
6.000 0.8305 0.00936 0.00427 -0.0203 0.4051 0.9725
6.250 0.8659 0.00981 0.00457 -0.0224 0.3675 0.9792
6.500 0.8990 0.01038 0.00495 -0.0241 0.3276 0.9865
6.750 0.9325 0.01104 0.00541 -0.0260 0.2872 0.9931
7.000 0.9681 0.01170 0.00587 -0.0285 0.2498 0.9985
7.500 1.0012 0.01255 0.00655 -0.0251 0.2142 1.0000
7.750 1.0145 0.01289 0.00685 -0.0226 0.2024 1.0000
8.000 1.0275 0.01325 0.00718 -0.0200 0.1917 1.0000
8.250 1.0394 0.01365 0.00753 -0.0173 0.1811 1.0000
8.500 1.0535 0.01398 0.00786 -0.0150 0.1713 1.0000
8.750 1.0658 0.01437 0.00822 -0.0124 0.1616 1.0000
9.250 1.0867 0.01519 0.00899 -0.0065 0.1432 1.0000
9.500 1.0934 0.01562 0.00941 -0.0030 0.1352 1.0000
9.750 1.1016 0.01609 0.00986 0.0002 0.1267 1.0000
10.000 1.1111 0.01661 0.01038 0.0029 0.1184 1.0000
10.250 1.1192 0.01725 0.01099 0.0056 0.1099 1.0000
10.500 1.1280 0.01794 0.01166 0.0080 0.1003 1.0000
10.750 1.1368 0.01872 0.01242 0.0102 0.0908 1.0000
11.000 1.1436 0.01967 0.01334 0.0124 0.0798 1.0000
11.250 1.1485 0.02084 0.01444 0.0146 0.0682 1.0000
11.500 1.1526 0.02218 0.01573 0.0165 0.0583 1.0000
11.750 1.1574 0.02358 0.01711 0.0182 0.0512 1.0000
12.000 1.1622 0.02507 0.01861 0.0196 0.0458 1.0000
12.250 1.1663 0.02671 0.02025 0.0209 0.0422 1.0000
12.500 1.1738 0.02815 0.02174 0.0218 0.0398 1.0000
12.750 1.1771 0.02996 0.02358 0.0228 0.0377 1.0000
13.000 1.1803 0.03186 0.02553 0.0236 0.0364 1.0000
13.250 1.1869 0.03351 0.02727 0.0243 0.0350 1.0000
13.500 1.1920 0.03532 0.02913 0.0248 0.0337 1.0000
13.750 1.1942 0.03744 0.03130 0.0253 0.0327 1.0000
14.000 1.1903 0.04014 0.03404 0.0259 0.0315 1.0000
14.250 1.1940 0.04222 0.03620 0.0262 0.0309 1.0000
14.500 1.1971 0.04442 0.03849 0.0264 0.0303 1.0000
14.750 1.2014 0.04655 0.04070 0.0264 0.0292 1.0000
15.000 1.2029 0.04902 0.04324 0.0264 0.0285 1.0000
15.250 1.2023 0.05180 0.04608 0.0263 0.0278 1.0000
15.500 1.1990 0.05490 0.04921 0.0260 0.0271 1.0000
15.750 1.1942 0.05818 0.05256 0.0258 0.0265 1.0000
16.000 1.1963 0.06087 0.05535 0.0254 0.0261 1.0000
16.250 1.1977 0.06371 0.05829 0.0248 0.0255 1.0000
16.500 1.1974 0.06672 0.06139 0.0243 0.0251 1.0000
16.750 1.1978 0.06978 0.06453 0.0235 0.0244 1.0000
17.000 1.1967 0.07306 0.06787 0.0226 0.0238 1.0000
17.250 1.1940 0.07656 0.07143 0.0217 0.0233 1.0000
17.500 1.1890 0.08026 0.07516 0.0208 0.0228 1.0000
17.750 1.1852 0.08377 0.07873 0.0201 0.0224 1.0000
18.000 1.1835 0.08733 0.08241 0.0189 0.0221 1.0000
18.250 1.1810 0.09116 0.08635 0.0174 0.0217 1.0000
18.500 1.1781 0.09486 0.09014 0.0163 0.0215 1.0000
18.750 1.1741 0.09897 0.09436 0.0146 0.0210 1.0000
19.000 1.1711 0.10285 0.09832 0.0131 0.0206 1.0000
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