KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 200,000 Max Cl/Cd: 62.85 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135b-il-200000-n5.txt Download as CSV file: xf-kc135b-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4922 0.10787 0.10404 -0.0304 1.0000 0.0245
-11.500 -0.4887 0.10471 0.10090 -0.0307 1.0000 0.0239
-11.000 -0.5326 0.08195 0.07814 -0.0457 1.0000 0.0200
-10.750 -0.5409 0.07742 0.07360 -0.0482 1.0000 0.0199
-10.500 -0.5587 0.07205 0.06818 -0.0512 1.0000 0.0198
-10.250 -0.5719 0.06832 0.06440 -0.0524 1.0000 0.0196
-10.000 -0.5942 0.06420 0.06018 -0.0524 1.0000 0.0196
-9.750 -0.6100 0.06148 0.05739 -0.0504 1.0000 0.0195
-9.500 -0.6286 0.05868 0.05449 -0.0470 1.0000 0.0195
-9.250 -0.6466 0.05489 0.05048 -0.0434 1.0000 0.0198
-9.000 -0.6626 0.05085 0.04613 -0.0391 1.0000 0.0200
-8.500 -0.6598 0.04641 0.04150 -0.0347 0.9955 0.0205
-8.250 -0.6403 0.04340 0.03826 -0.0360 0.9826 0.0208
-8.000 -0.6216 0.03923 0.03369 -0.0366 0.9695 0.0208
-7.750 -0.5995 0.03589 0.02999 -0.0373 0.9564 0.0209
-7.500 -0.5747 0.03308 0.02684 -0.0380 0.9436 0.0212
-7.250 -0.5477 0.03052 0.02395 -0.0388 0.9311 0.0216
-7.000 -0.5197 0.02833 0.02144 -0.0395 0.9181 0.0223
-6.750 -0.4922 0.02639 0.01916 -0.0398 0.9045 0.0234
-6.500 -0.4645 0.02437 0.01677 -0.0398 0.8913 0.0240
-6.250 -0.4364 0.02268 0.01476 -0.0399 0.8789 0.0245
-6.000 -0.4084 0.02128 0.01312 -0.0399 0.8673 0.0250
-5.750 -0.3822 0.02012 0.01189 -0.0398 0.8559 0.0257
-5.500 -0.3572 0.01931 0.01099 -0.0394 0.8448 0.0264
-5.250 -0.3323 0.01858 0.01017 -0.0389 0.8350 0.0273
-5.000 -0.3079 0.01802 0.00952 -0.0383 0.8253 0.0292
-4.750 -0.2839 0.01740 0.00877 -0.0375 0.8166 0.0307
-4.500 -0.2620 0.01662 0.00794 -0.0365 0.8083 0.0318
-4.250 -0.2403 0.01605 0.00736 -0.0355 0.8004 0.0332
-4.000 -0.2179 0.01560 0.00686 -0.0345 0.7929 0.0351
-3.750 -0.1951 0.01522 0.00641 -0.0336 0.7859 0.0378
-3.500 -0.1739 0.01471 0.00586 -0.0325 0.7788 0.0404
-3.250 -0.1514 0.01433 0.00543 -0.0316 0.7729 0.0434
-3.000 -0.1279 0.01405 0.00508 -0.0308 0.7661 0.0476
-2.750 -0.1050 0.01370 0.00467 -0.0299 0.7602 0.0529
-2.500 -0.0807 0.01346 0.00437 -0.0293 0.7544 0.0597
-2.250 -0.0570 0.01317 0.00407 -0.0286 0.7484 0.0718
-2.000 -0.0359 0.01261 0.00373 -0.0275 0.7432 0.1418
-1.750 -0.0345 0.01080 0.00356 -0.0231 0.7372 0.5692
-1.500 -0.0112 0.01074 0.00360 -0.0220 0.7316 0.6208
-1.250 0.0135 0.01073 0.00359 -0.0211 0.7270 0.6523
-1.000 0.0383 0.01072 0.00361 -0.0204 0.7215 0.6766
-0.750 0.0635 0.01070 0.00364 -0.0197 0.7160 0.6972
-0.500 0.0891 0.01070 0.00365 -0.0190 0.7115 0.7163
-0.250 0.1154 0.01070 0.00365 -0.0186 0.7066 0.7290
0.000 0.1423 0.01070 0.00364 -0.0184 0.7011 0.7360
0.250 0.1696 0.01070 0.00360 -0.0183 0.6963 0.7425
0.500 0.1967 0.01070 0.00361 -0.0182 0.6908 0.7496
0.750 0.2233 0.01070 0.00361 -0.0179 0.6842 0.7575
1.000 0.2507 0.01069 0.00359 -0.0178 0.6785 0.7651
1.250 0.2771 0.01069 0.00364 -0.0175 0.6711 0.7740
1.500 0.3041 0.01069 0.00366 -0.0173 0.6651 0.7837
1.750 0.3309 0.01069 0.00371 -0.0170 0.6584 0.7941
2.000 0.3574 0.01067 0.00371 -0.0167 0.6490 0.8059
2.250 0.3836 0.01064 0.00371 -0.0162 0.6360 0.8185
2.500 0.4104 0.01062 0.00374 -0.0159 0.6233 0.8326
2.750 0.4386 0.01064 0.00379 -0.0158 0.6144 0.8479
3.000 0.4679 0.01067 0.00390 -0.0161 0.6049 0.8641
3.250 0.4986 0.01073 0.00402 -0.0166 0.5951 0.8805
3.500 0.5309 0.01080 0.00412 -0.0176 0.5850 0.8968
3.750 0.5645 0.01088 0.00426 -0.0188 0.5722 0.9123
4.000 0.5990 0.01098 0.00441 -0.0202 0.5577 0.9262
4.250 0.6332 0.01110 0.00455 -0.0217 0.5417 0.9391
4.500 0.6665 0.01123 0.00469 -0.0229 0.5214 0.9515
4.750 0.6989 0.01142 0.00485 -0.0240 0.4946 0.9633
5.000 0.7316 0.01167 0.00502 -0.0253 0.4568 0.9734
5.250 0.7617 0.01212 0.00525 -0.0262 0.4015 0.9837
5.500 0.7908 0.01279 0.00563 -0.0273 0.3418 0.9938
5.750 0.8161 0.01342 0.00607 -0.0275 0.3041 1.0000
6.000 0.8289 0.01394 0.00646 -0.0251 0.2756 1.0000
6.250 0.8416 0.01449 0.00687 -0.0226 0.2439 1.0000
6.500 0.8544 0.01505 0.00728 -0.0202 0.2160 1.0000
6.750 0.8687 0.01556 0.00769 -0.0180 0.1951 1.0000
7.000 0.8834 0.01605 0.00812 -0.0160 0.1785 1.0000
7.250 0.8982 0.01653 0.00857 -0.0139 0.1632 1.0000
7.500 0.9130 0.01702 0.00903 -0.0119 0.1484 1.0000
7.750 0.9273 0.01754 0.00951 -0.0098 0.1322 1.0000
8.000 0.9416 0.01808 0.01001 -0.0077 0.1143 1.0000
8.250 0.9533 0.01875 0.01059 -0.0054 0.0939 1.0000
8.500 0.9636 0.01950 0.01124 -0.0028 0.0750 1.0000
8.750 0.9709 0.02031 0.01196 0.0002 0.0603 1.0000
9.000 0.9791 0.02108 0.01271 0.0031 0.0517 1.0000
9.250 0.9876 0.02190 0.01355 0.0057 0.0461 1.0000
9.500 0.9961 0.02279 0.01446 0.0082 0.0417 1.0000
9.750 1.0048 0.02373 0.01544 0.0104 0.0383 1.0000
10.000 1.0143 0.02466 0.01645 0.0124 0.0357 1.0000
10.250 1.0216 0.02579 0.01760 0.0144 0.0334 1.0000
10.500 1.0285 0.02699 0.01888 0.0163 0.0316 1.0000
10.750 1.0372 0.02814 0.02012 0.0179 0.0301 1.0000
11.000 1.0451 0.02939 0.02148 0.0194 0.0286 1.0000
11.250 1.0516 0.03080 0.02296 0.0208 0.0274 1.0000
11.500 1.0548 0.03252 0.02472 0.0222 0.0263 1.0000
11.750 1.0608 0.03411 0.02640 0.0234 0.0254 1.0000
12.000 1.0683 0.03562 0.02804 0.0244 0.0241 1.0000
12.250 1.0749 0.03724 0.02976 0.0252 0.0230 1.0000
12.500 1.0795 0.03908 0.03169 0.0261 0.0224 1.0000
12.750 1.0836 0.04101 0.03370 0.0268 0.0217 1.0000
13.000 1.0852 0.04323 0.03597 0.0275 0.0210 1.0000
13.250 1.0880 0.04543 0.03825 0.0281 0.0206 1.0000
13.500 1.0921 0.04756 0.04054 0.0286 0.0201 1.0000
13.750 1.0952 0.04985 0.04298 0.0290 0.0196 1.0000
14.000 1.0971 0.05229 0.04556 0.0292 0.0189 1.0000
14.250 1.0983 0.05488 0.04829 0.0293 0.0184 1.0000
14.500 1.0985 0.05759 0.05111 0.0289 0.0178 1.0000
14.750 1.0982 0.06046 0.05408 0.0284 0.0173 1.0000
15.000 1.0968 0.06359 0.05731 0.0280 0.0170 1.0000
15.250 1.0951 0.06682 0.06063 0.0273 0.0167 1.0000
15.500 1.0922 0.07031 0.06419 0.0266 0.0164 1.0000
15.750 1.0879 0.07420 0.06825 0.0255 0.0163 1.0000
16.000 1.0793 0.07896 0.07325 0.0237 0.0159 1.0000
16.250 1.0725 0.08353 0.07799 0.0219 0.0159 1.0000
16.500 1.0624 0.08885 0.08352 0.0196 0.0157 1.0000
16.750 1.0494 0.09495 0.08982 0.0167 0.0155 1.0000
17.000 1.0373 0.10111 0.09616 0.0135 0.0155 1.0000
17.250 1.0222 0.10813 0.10337 0.0096 0.0154 1.0000
17.500 1.0052 0.11586 0.11128 0.0053 0.0154 1.0000
17.750 0.9852 0.12460 0.12022 0.0002 0.0154 1.0000
18.000 0.9625 0.13436 0.13016 -0.0056 0.0155 1.0000
18.250 0.9308 0.14704 0.14303 -0.0131 0.0156 1.0000
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Polar data table (+)
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