KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il) Reynolds number: 200,000 Max Cl/Cd: 66 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135c-il-200000-n5.txt Download as CSV file: xf-kc135c-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL200.76 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4754 0.08538 0.08183 -0.0337 1.0000 0.0225
-9.000 -0.4815 0.08027 0.07677 -0.0376 1.0000 0.0227
-8.750 -0.4946 0.07519 0.07169 -0.0416 1.0000 0.0223
-8.500 -0.5095 0.07163 0.06811 -0.0418 1.0000 0.0222
-8.250 -0.5226 0.06793 0.06435 -0.0412 1.0000 0.0217
-8.000 -0.5290 0.06472 0.06109 -0.0400 1.0000 0.0219
-7.750 -0.5358 0.06071 0.05693 -0.0381 1.0000 0.0190
-7.500 -0.5398 0.05774 0.05389 -0.0359 1.0000 0.0184
-7.250 -0.5348 0.05406 0.05000 -0.0350 0.9953 0.0191
-7.000 -0.5151 0.04944 0.04507 -0.0369 0.9841 0.0193
-6.750 -0.4945 0.04509 0.04042 -0.0383 0.9739 0.0192
-6.500 -0.4723 0.04126 0.03632 -0.0396 0.9645 0.0186
-6.250 -0.4495 0.03740 0.03210 -0.0401 0.9540 0.0183
-6.000 -0.4256 0.03391 0.02823 -0.0403 0.9437 0.0182
-5.750 -0.3997 0.03062 0.02453 -0.0404 0.9344 0.0184
-5.500 -0.3713 0.02795 0.02129 -0.0399 0.9249 0.0200
-5.250 -0.3452 0.02570 0.01866 -0.0396 0.9151 0.0202
-5.000 -0.3185 0.02316 0.01580 -0.0396 0.9064 0.0204
-4.750 -0.2921 0.02128 0.01370 -0.0395 0.8970 0.0210
-4.500 -0.2650 0.01995 0.01219 -0.0394 0.8878 0.0215
-4.250 -0.2374 0.01893 0.01101 -0.0393 0.8796 0.0225
-4.000 -0.2112 0.01817 0.01013 -0.0390 0.8706 0.0242
-3.750 -0.1842 0.01719 0.00901 -0.0387 0.8629 0.0253
-3.500 -0.1586 0.01627 0.00797 -0.0381 0.8543 0.0261
-3.250 -0.1334 0.01552 0.00710 -0.0374 0.8468 0.0269
-3.000 -0.1104 0.01468 0.00622 -0.0365 0.8391 0.0281
-2.750 -0.0874 0.01407 0.00560 -0.0357 0.8321 0.0303
-2.500 -0.0634 0.01370 0.00521 -0.0350 0.8245 0.0337
-2.250 -0.0394 0.01329 0.00471 -0.0342 0.8182 0.0363
-2.000 -0.0165 0.01283 0.00418 -0.0333 0.8110 0.0398
-1.750 0.0085 0.01257 0.00386 -0.0328 0.8054 0.0470
-1.500 0.0329 0.01229 0.00352 -0.0322 0.7983 0.0552
-1.250 0.0578 0.01203 0.00326 -0.0316 0.7924 0.0759
-1.000 0.0617 0.00994 0.00306 -0.0277 0.7857 0.6071
-0.750 0.0822 0.00971 0.00313 -0.0258 0.7795 0.7049
-0.500 0.1064 0.00963 0.00313 -0.0248 0.7742 0.7464
-0.250 0.1305 0.00956 0.00318 -0.0237 0.7679 0.7842
0.000 0.1555 0.00953 0.00323 -0.0226 0.7626 0.8210
0.250 0.1823 0.00953 0.00327 -0.0222 0.7565 0.8421
0.500 0.2104 0.00953 0.00323 -0.0221 0.7495 0.8535
0.750 0.2387 0.00953 0.00322 -0.0222 0.7412 0.8654
1.250 0.2980 0.00954 0.00315 -0.0226 0.7197 0.8904
1.500 0.3291 0.00956 0.00313 -0.0232 0.7058 0.9023
1.750 0.3614 0.00960 0.00316 -0.0241 0.6940 0.9140
2.000 0.3946 0.00966 0.00321 -0.0252 0.6859 0.9256
2.250 0.4275 0.00972 0.00329 -0.0263 0.6762 0.9372
2.500 0.4628 0.00978 0.00337 -0.0280 0.6662 0.9461
2.750 0.4966 0.00985 0.00346 -0.0293 0.6549 0.9555
3.000 0.5296 0.00992 0.00354 -0.0305 0.6427 0.9655
3.250 0.5648 0.00998 0.00362 -0.0322 0.6273 0.9731
3.500 0.5990 0.01005 0.00373 -0.0337 0.6083 0.9809
3.750 0.6327 0.01015 0.00381 -0.0351 0.5844 0.9886
4.000 0.6667 0.01028 0.00390 -0.0366 0.5507 0.9960
4.250 0.6937 0.01051 0.00400 -0.0367 0.5037 1.0000
4.500 0.7084 0.01094 0.00415 -0.0343 0.4399 1.0000
4.750 0.7206 0.01162 0.00445 -0.0316 0.3679 1.0000
5.000 0.7339 0.01232 0.00484 -0.0292 0.3093 1.0000
5.500 0.7658 0.01349 0.00562 -0.0254 0.2304 1.0000
5.750 0.7834 0.01399 0.00604 -0.0238 0.2044 1.0000
6.000 0.8018 0.01445 0.00644 -0.0223 0.1797 1.0000
6.250 0.8200 0.01494 0.00685 -0.0208 0.1508 1.0000
6.500 0.8354 0.01567 0.00735 -0.0189 0.1076 1.0000
6.750 0.8487 0.01662 0.00805 -0.0168 0.0648 1.0000
7.000 0.8638 0.01747 0.00878 -0.0149 0.0475 1.0000
7.250 0.8803 0.01820 0.00952 -0.0132 0.0395 1.0000
7.500 0.8970 0.01892 0.01030 -0.0115 0.0347 1.0000
7.750 0.9134 0.01964 0.01109 -0.0098 0.0307 1.0000
8.000 0.9266 0.02060 0.01211 -0.0078 0.0276 1.0000
8.250 0.9420 0.02138 0.01302 -0.0059 0.0257 1.0000
8.500 0.9561 0.02223 0.01398 -0.0040 0.0240 1.0000
8.750 0.9695 0.02313 0.01494 -0.0021 0.0222 1.0000
9.000 0.9778 0.02434 0.01618 0.0004 0.0205 1.0000
9.250 0.9891 0.02533 0.01729 0.0027 0.0195 1.0000
9.500 1.0003 0.02639 0.01847 0.0049 0.0185 1.0000
9.750 1.0113 0.02756 0.01976 0.0069 0.0177 1.0000
10.000 1.0223 0.02878 0.02109 0.0088 0.0168 1.0000
10.250 1.0330 0.03011 0.02251 0.0106 0.0162 1.0000
10.500 1.0435 0.03151 0.02402 0.0123 0.0157 1.0000
10.750 1.0525 0.03312 0.02570 0.0140 0.0151 1.0000
11.000 1.0611 0.03518 0.02788 0.0155 0.0146 1.0000
11.250 1.0690 0.03679 0.02975 0.0171 0.0141 1.0000
11.500 1.0748 0.03855 0.03175 0.0188 0.0135 1.0000
11.750 1.0786 0.04064 0.03407 0.0203 0.0131 1.0000
12.000 1.0799 0.04301 0.03667 0.0218 0.0128 1.0000
12.250 1.0788 0.04555 0.03944 0.0230 0.0125 1.0000
12.500 1.0752 0.04842 0.04254 0.0241 0.0124 1.0000
12.750 1.0695 0.05145 0.04579 0.0248 0.0121 1.0000
13.000 1.0607 0.05503 0.04960 0.0251 0.0121 1.0000
13.250 1.0497 0.05902 0.05381 0.0248 0.0120 1.0000
13.500 1.0380 0.06321 0.05821 0.0240 0.0119 1.0000
13.750 1.0225 0.06829 0.06352 0.0224 0.0119 1.0000
14.000 1.0045 0.07413 0.06956 0.0200 0.0119 1.0000
14.250 0.9859 0.08057 0.07620 0.0167 0.0118 1.0000
14.500 0.9643 0.08839 0.08422 0.0121 0.0119 1.0000
14.750 0.9324 0.09959 0.09566 0.0049 0.0123 1.0000
15.000 0.8989 0.11284 0.10909 -0.0035 0.0124 1.0000
15.250 0.8465 0.13308 0.12943 -0.0149 0.0131 1.0000
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Polar data table (+)
Polar graphs
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