KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 500,000 Max Cl/Cd: 100.7 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135d-il-500000.txt Download as CSV file: xf-kc135d-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL351.6 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4422 0.08339 0.08117 -0.0298 1.0000 0.0126
-8.250 -0.4446 0.07966 0.07748 -0.0319 1.0000 0.0126
-8.000 -0.4529 0.07586 0.07373 -0.0346 1.0000 0.0127
-7.750 -0.4607 0.07217 0.07003 -0.0364 1.0000 0.0127
-7.500 -0.4639 0.06858 0.06642 -0.0373 1.0000 0.0128
-7.250 -0.4667 0.06535 0.06317 -0.0372 1.0000 0.0129
-7.000 -0.4729 0.06268 0.06048 -0.0354 1.0000 0.0131
-6.750 -0.4586 0.05829 0.05598 -0.0384 0.9966 0.0136
-6.500 -0.4298 0.05331 0.05080 -0.0430 0.9907 0.0149
-6.250 -0.3930 0.04969 0.04685 -0.0462 0.9854 0.0156
-6.000 -0.3653 0.04562 0.04252 -0.0485 0.9796 0.0157
-5.750 -0.3473 0.03821 0.03484 -0.0513 0.9732 0.0164
-5.500 -0.3202 0.03514 0.03163 -0.0536 0.9682 0.0170
-5.250 -0.2941 0.03304 0.02943 -0.0550 0.9602 0.0184
-5.000 -0.2646 0.03057 0.02672 -0.0559 0.9529 0.0202
-4.750 -0.2304 0.03024 0.02606 -0.0554 0.9441 0.0224
-4.500 -0.2059 0.02843 0.02396 -0.0547 0.9331 0.0226
-4.250 -0.1831 0.02636 0.02159 -0.0537 0.9225 0.0227
-2.500 -0.0162 0.01264 0.00640 -0.0474 0.8599 0.0278
-2.250 0.0098 0.01193 0.00561 -0.0468 0.8524 0.0293
-2.000 0.0353 0.01123 0.00483 -0.0461 0.8449 0.0303
-1.750 0.0602 0.01059 0.00413 -0.0454 0.8375 0.0310
-1.500 0.0852 0.01016 0.00364 -0.0447 0.8303 0.0320
-1.250 0.1099 0.00974 0.00317 -0.0441 0.8228 0.0336
-1.000 0.1337 0.00919 0.00254 -0.0432 0.8152 0.0365
-0.750 0.1591 0.00892 0.00223 -0.0427 0.8067 0.0396
-0.500 0.1852 0.00874 0.00197 -0.0422 0.7984 0.0434
-0.250 0.2109 0.00856 0.00174 -0.0417 0.7878 0.0532
0.000 0.2204 0.00655 0.00158 -0.0387 0.7774 0.6717
0.250 0.2372 0.00602 0.00163 -0.0358 0.7682 0.8347
0.500 0.2699 0.00590 0.00171 -0.0363 0.7596 0.9297
0.750 0.3132 0.00596 0.00176 -0.0394 0.7516 0.9587
1.000 0.3618 0.00608 0.00180 -0.0438 0.7431 0.9761
1.250 0.4040 0.00614 0.00184 -0.0470 0.7332 0.9853
1.500 0.4430 0.00618 0.00183 -0.0496 0.7235 0.9905
1.750 0.4809 0.00623 0.00182 -0.0519 0.7147 0.9955
2.000 0.5203 0.00624 0.00183 -0.0546 0.7038 0.9999
2.250 0.5435 0.00626 0.00183 -0.0538 0.6932 1.0000
2.500 0.5664 0.00629 0.00185 -0.0529 0.6818 1.0000
2.750 0.5893 0.00635 0.00188 -0.0519 0.6694 1.0000
3.000 0.6124 0.00641 0.00193 -0.0510 0.6555 1.0000
3.250 0.6354 0.00648 0.00200 -0.0500 0.6389 1.0000
3.500 0.6580 0.00659 0.00206 -0.0490 0.6178 1.0000
3.750 0.6797 0.00675 0.00213 -0.0477 0.5844 1.0000
4.000 0.6992 0.00704 0.00223 -0.0461 0.5283 1.0000
4.250 0.7151 0.00765 0.00245 -0.0439 0.4385 1.0000
4.500 0.7302 0.00843 0.00279 -0.0418 0.3431 1.0000
4.750 0.7479 0.00907 0.00314 -0.0401 0.2842 1.0000
5.000 0.7685 0.00949 0.00343 -0.0389 0.2501 1.0000
5.250 0.7895 0.00989 0.00371 -0.0378 0.2196 1.0000
5.500 0.8102 0.01032 0.00403 -0.0367 0.1880 1.0000
5.750 0.8295 0.01089 0.00438 -0.0353 0.1406 1.0000
6.000 0.8406 0.01223 0.00513 -0.0328 0.0452 1.0000
6.250 0.8591 0.01297 0.00583 -0.0311 0.0307 1.0000
6.500 0.8796 0.01352 0.00644 -0.0299 0.0263 1.0000
6.750 0.8952 0.01458 0.00760 -0.0278 0.0221 1.0000
7.000 0.9165 0.01505 0.00813 -0.0267 0.0203 1.0000
7.250 0.9357 0.01572 0.00887 -0.0253 0.0185 1.0000
7.500 0.9536 0.01652 0.00972 -0.0238 0.0172 1.0000
7.750 0.9683 0.01768 0.01096 -0.0217 0.0161 1.0000
8.000 0.9774 0.01998 0.01339 -0.0188 0.0152 1.0000
8.250 0.9976 0.02069 0.01422 -0.0177 0.0147 1.0000
8.500 1.0161 0.02197 0.01562 -0.0163 0.0144 1.0000
8.750 1.0351 0.02311 0.01689 -0.0150 0.0138 1.0000
9.000 1.0535 0.02432 0.01822 -0.0138 0.0131 1.0000
9.250 1.0711 0.02595 0.02001 -0.0124 0.0127 1.0000
9.500 1.0876 0.02762 0.02185 -0.0110 0.0124 1.0000
9.750 1.1020 0.02966 0.02413 -0.0093 0.0122 1.0000
10.000 1.1136 0.03191 0.02662 -0.0074 0.0120 1.0000
10.250 1.1190 0.03506 0.03012 -0.0047 0.0121 1.0000
10.500 1.1174 0.03856 0.03400 -0.0013 0.0122 1.0000
10.750 1.1009 0.04326 0.03912 0.0037 0.0130 1.0000
11.000 1.0815 0.04700 0.04315 0.0082 0.0135 1.0000
11.250 1.0579 0.05127 0.04766 0.0116 0.0142 1.0000
11.500 1.0317 0.05624 0.05282 0.0137 0.0147 1.0000
11.750 0.9517 0.04910 0.04599 0.0164 0.0140 1.0000
12.000 0.9270 0.05487 0.05193 0.0159 0.0142 1.0000
12.250 0.9024 0.06117 0.05838 0.0144 0.0142 1.0000
12.500 0.8786 0.06792 0.06527 0.0120 0.0143 1.0000
12.750 0.8548 0.07527 0.07276 0.0086 0.0143 1.0000
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Polar data table (+)
Polar graphs
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