KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.76 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135b-il-1000000-n5.txt Download as CSV file: xf-kc135b-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9829 0.03102 0.02761 -0.0465 1.0000 0.0092
-12.000 -0.9895 0.02868 0.02503 -0.0423 1.0000 0.0093
-11.750 -0.9867 0.02673 0.02285 -0.0394 1.0000 0.0095
-11.500 -0.9785 0.02530 0.02125 -0.0369 1.0000 0.0096
-11.250 -0.9693 0.02396 0.01974 -0.0344 1.0000 0.0097
-10.750 -0.9279 0.02152 0.01699 -0.0337 0.9865 0.0099
-10.500 -0.8962 0.02049 0.01583 -0.0355 0.9770 0.0100
-10.250 -0.8617 0.01885 0.01399 -0.0382 0.9652 0.0103
-9.750 -0.7849 0.01712 0.01203 -0.0443 0.9188 0.0107
-9.500 -0.7623 0.01672 0.01146 -0.0436 0.8838 0.0109
-9.250 -0.7424 0.01639 0.01099 -0.0423 0.8562 0.0111
-9.000 -0.7225 0.01599 0.01045 -0.0410 0.8350 0.0113
-8.750 -0.7022 0.01554 0.00988 -0.0398 0.8176 0.0115
-8.500 -0.6817 0.01504 0.00926 -0.0386 0.8032 0.0116
-8.000 -0.6391 0.01414 0.00817 -0.0366 0.7805 0.0120
-7.750 -0.6174 0.01373 0.00766 -0.0356 0.7711 0.0122
-7.500 -0.5953 0.01332 0.00717 -0.0346 0.7626 0.0124
-7.250 -0.5728 0.01296 0.00673 -0.0338 0.7552 0.0126
-7.000 -0.5501 0.01259 0.00629 -0.0329 0.7481 0.0127
-6.750 -0.5271 0.01227 0.00590 -0.0321 0.7415 0.0128
-6.500 -0.5051 0.01182 0.00540 -0.0311 0.7356 0.0132
-6.250 -0.4819 0.01149 0.00503 -0.0303 0.7298 0.0136
-6.000 -0.4576 0.01125 0.00476 -0.0298 0.7246 0.0140
-5.750 -0.4329 0.01101 0.00449 -0.0292 0.7193 0.0145
-5.500 -0.4085 0.01076 0.00420 -0.0286 0.7141 0.0149
-5.250 -0.3839 0.01054 0.00393 -0.0281 0.7095 0.0152
-5.000 -0.3586 0.01032 0.00368 -0.0276 0.7047 0.0158
-4.750 -0.3335 0.01010 0.00342 -0.0272 0.6999 0.0163
-4.500 -0.3086 0.00988 0.00318 -0.0267 0.6953 0.0172
-4.250 -0.2828 0.00970 0.00299 -0.0263 0.6910 0.0180
-4.000 -0.2567 0.00954 0.00282 -0.0260 0.6862 0.0191
-3.750 -0.2306 0.00940 0.00265 -0.0257 0.6816 0.0200
-3.500 -0.2047 0.00924 0.00247 -0.0254 0.6774 0.0215
-3.250 -0.1782 0.00910 0.00233 -0.0251 0.6730 0.0232
-3.000 -0.1515 0.00899 0.00221 -0.0249 0.6681 0.0248
-2.750 -0.1253 0.00885 0.00207 -0.0247 0.6635 0.0276
-2.500 -0.0984 0.00874 0.00196 -0.0245 0.6595 0.0300
-2.250 -0.0716 0.00863 0.00185 -0.0243 0.6548 0.0331
-2.000 -0.0450 0.00853 0.00175 -0.0241 0.6494 0.0372
-1.750 -0.0182 0.00844 0.00166 -0.0239 0.6438 0.0425
-1.500 0.0087 0.00834 0.00158 -0.0238 0.6375 0.0497
-1.250 0.0351 0.00824 0.00150 -0.0235 0.6322 0.0650
-1.000 0.0519 0.00717 0.00121 -0.0219 0.6274 0.3235
-0.750 0.0692 0.00630 0.00105 -0.0202 0.6214 0.5297
-0.500 0.0954 0.00622 0.00104 -0.0199 0.6154 0.5641
-0.250 0.1223 0.00615 0.00104 -0.0197 0.6102 0.5898
0.000 0.1496 0.00615 0.00104 -0.0196 0.6039 0.6013
0.250 0.1769 0.00615 0.00104 -0.0195 0.5956 0.6139
0.500 0.2034 0.00617 0.00104 -0.0192 0.5835 0.6296
1.000 0.2574 0.00623 0.00106 -0.0189 0.5584 0.6466
1.250 0.2848 0.00626 0.00108 -0.0188 0.5493 0.6510
1.500 0.3120 0.00631 0.00110 -0.0188 0.5398 0.6556
2.000 0.3664 0.00641 0.00117 -0.0186 0.5160 0.6642
2.250 0.3933 0.00648 0.00121 -0.0184 0.5037 0.6693
2.500 0.4202 0.00656 0.00127 -0.0183 0.4912 0.6745
2.750 0.4466 0.00664 0.00133 -0.0181 0.4754 0.6800
3.000 0.4724 0.00677 0.00141 -0.0178 0.4536 0.6861
3.500 0.5209 0.00723 0.00165 -0.0166 0.3827 0.6989
3.750 0.5429 0.00762 0.00185 -0.0157 0.3323 0.7070
4.000 0.5660 0.00791 0.00204 -0.0150 0.3012 0.7159
4.250 0.5901 0.00812 0.00221 -0.0144 0.2798 0.7254
4.500 0.6144 0.00830 0.00236 -0.0139 0.2589 0.7364
4.750 0.6380 0.00851 0.00253 -0.0132 0.2373 0.7489
5.000 0.6591 0.00885 0.00276 -0.0121 0.2021 0.7643
5.250 0.6808 0.00912 0.00298 -0.0111 0.1778 0.7829
5.750 0.7250 0.00947 0.00339 -0.0092 0.1488 0.8300
6.000 0.7471 0.00958 0.00358 -0.0082 0.1395 0.8610
6.250 0.7693 0.00974 0.00381 -0.0072 0.1275 0.8976
6.500 0.7974 0.01001 0.00411 -0.0075 0.1110 0.9332
6.750 0.8351 0.01047 0.00449 -0.0103 0.0893 0.9553
7.000 0.8726 0.01100 0.00492 -0.0131 0.0686 0.9686
7.250 0.9068 0.01158 0.00538 -0.0152 0.0485 0.9780
7.500 0.9365 0.01211 0.00583 -0.0162 0.0350 0.9860
7.750 0.9658 0.01253 0.00623 -0.0171 0.0289 0.9922
8.000 0.9930 0.01294 0.00663 -0.0175 0.0255 0.9989
8.250 1.0165 0.01329 0.00698 -0.0171 0.0232 1.0000
8.500 1.0331 0.01366 0.00734 -0.0152 0.0212 1.0000
8.750 1.0508 0.01398 0.00768 -0.0135 0.0201 1.0000
9.000 1.0682 0.01430 0.00803 -0.0118 0.0191 1.0000
9.250 1.0847 0.01467 0.00841 -0.0100 0.0180 1.0000
9.500 1.1002 0.01508 0.00883 -0.0080 0.0169 1.0000
9.750 1.1141 0.01546 0.00924 -0.0058 0.0161 1.0000
10.000 1.1271 0.01581 0.00963 -0.0033 0.0155 1.0000
10.250 1.1400 0.01622 0.01006 -0.0009 0.0147 1.0000
10.500 1.1530 0.01668 0.01054 0.0013 0.0140 1.0000
10.750 1.1659 0.01720 0.01109 0.0033 0.0133 1.0000
11.000 1.1791 0.01774 0.01167 0.0052 0.0127 1.0000
11.250 1.1933 0.01828 0.01226 0.0069 0.0123 1.0000
11.500 1.2069 0.01888 0.01291 0.0085 0.0118 1.0000
11.750 1.2204 0.01953 0.01359 0.0100 0.0112 1.0000
12.000 1.2330 0.02027 0.01436 0.0115 0.0107 1.0000
12.250 1.2446 0.02111 0.01524 0.0130 0.0101 1.0000
12.500 1.2566 0.02197 0.01615 0.0143 0.0099 1.0000
12.750 1.2692 0.02283 0.01708 0.0154 0.0095 1.0000
13.000 1.2814 0.02375 0.01805 0.0165 0.0089 1.0000
13.250 1.2926 0.02479 0.01914 0.0175 0.0087 1.0000
13.500 1.3029 0.02594 0.02035 0.0185 0.0085 1.0000
13.750 1.3132 0.02712 0.02158 0.0193 0.0082 1.0000
14.000 1.3212 0.02853 0.02304 0.0202 0.0078 1.0000
14.250 1.3277 0.03011 0.02469 0.0210 0.0076 1.0000
14.500 1.3363 0.03153 0.02619 0.0216 0.0075 1.0000
14.750 1.3448 0.03301 0.02774 0.0222 0.0073 1.0000
15.000 1.3505 0.03477 0.02958 0.0227 0.0072 1.0000
15.250 1.3558 0.03658 0.03147 0.0231 0.0070 1.0000
15.500 1.3590 0.03866 0.03363 0.0235 0.0069 1.0000
15.750 1.3613 0.04088 0.03594 0.0238 0.0069 1.0000
16.000 1.3649 0.04301 0.03814 0.0239 0.0066 1.0000
16.250 1.3658 0.04550 0.04073 0.0239 0.0066 1.0000
16.500 1.3655 0.04822 0.04354 0.0237 0.0065 1.0000
16.750 1.3638 0.05119 0.04659 0.0234 0.0063 1.0000
17.000 1.3622 0.05424 0.04975 0.0229 0.0063 1.0000
17.250 1.3596 0.05753 0.05311 0.0222 0.0061 1.0000
17.500 1.3529 0.06145 0.05715 0.0212 0.0062 1.0000
17.750 1.3469 0.06539 0.06119 0.0200 0.0060 1.0000
18.000 1.3370 0.07001 0.06592 0.0185 0.0060 1.0000
18.250 1.3229 0.07542 0.07145 0.0165 0.0059 1.0000
18.500 1.3101 0.08076 0.07691 0.0145 0.0058 1.0000
18.750 1.2907 0.08736 0.08364 0.0117 0.0057 1.0000
19.000 1.2788 0.09292 0.08931 0.0093 0.0058 1.0000
19.250 1.2531 0.10090 0.09743 0.0058 0.0057 1.0000
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Polar data table (+)
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