LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Reynolds number: 100,000 Max Cl/Cd: 42.04 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141a-il-100000-n5.txt Download as CSV file: xf-c141a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7264 0.07271 0.06664 -0.0685 1.0000 0.0397
-12.500 -0.7850 0.06351 0.05713 -0.0717 1.0000 0.0391
-12.250 -0.8170 0.05904 0.05247 -0.0706 1.0000 0.0391
-12.000 -0.8425 0.05590 0.04916 -0.0677 1.0000 0.0392
-11.750 -0.8655 0.05352 0.04662 -0.0635 1.0000 0.0394
-11.500 -0.8880 0.05166 0.04462 -0.0581 1.0000 0.0396
-11.250 -0.9077 0.05000 0.04282 -0.0524 1.0000 0.0398
-11.000 -0.9205 0.04811 0.04075 -0.0475 1.0000 0.0403
-10.750 -0.9299 0.04623 0.03866 -0.0430 1.0000 0.0409
-10.500 -0.9368 0.04428 0.03646 -0.0386 1.0000 0.0418
-10.250 -0.9422 0.04217 0.03398 -0.0344 1.0000 0.0429
-10.000 -0.9427 0.04019 0.03167 -0.0306 1.0000 0.0440
-9.750 -0.9343 0.03912 0.03056 -0.0281 1.0000 0.0450
-9.500 -0.9258 0.03795 0.02929 -0.0255 1.0000 0.0462
-9.250 -0.9168 0.03656 0.02771 -0.0229 1.0000 0.0476
-9.000 -0.9066 0.03510 0.02598 -0.0204 1.0000 0.0493
-8.750 -0.8948 0.03369 0.02429 -0.0180 1.0000 0.0513
-8.500 -0.8809 0.03279 0.02340 -0.0162 1.0000 0.0529
-8.250 -0.8663 0.03184 0.02235 -0.0143 1.0000 0.0549
-8.000 -0.8507 0.03079 0.02109 -0.0124 1.0000 0.0574
-7.750 -0.8343 0.02977 0.01992 -0.0108 1.0000 0.0599
-7.500 -0.8178 0.02899 0.01915 -0.0092 1.0000 0.0623
-7.250 -0.7976 0.02817 0.01822 -0.0082 0.9994 0.0654
-7.000 -0.7703 0.02727 0.01717 -0.0086 0.9971 0.0692
-6.750 -0.7428 0.02654 0.01645 -0.0092 0.9948 0.0731
-6.500 -0.7154 0.02585 0.01563 -0.0095 0.9925 0.0778
-6.250 -0.6895 0.02511 0.01492 -0.0097 0.9898 0.0824
-6.000 -0.6622 0.02452 0.01426 -0.0101 0.9871 0.0882
-5.750 -0.6342 0.02391 0.01365 -0.0107 0.9847 0.0945
-5.500 -0.6066 0.02341 0.01310 -0.0111 0.9821 0.1022
-5.250 -0.5819 0.02284 0.01258 -0.0109 0.9787 0.1106
-5.000 -0.5548 0.02234 0.01210 -0.0112 0.9756 0.1212
-4.750 -0.5258 0.02189 0.01168 -0.0120 0.9729 0.1352
-4.500 -0.4972 0.02144 0.01130 -0.0126 0.9702 0.1531
-4.250 -0.4737 0.02097 0.01093 -0.0122 0.9661 0.1762
-4.000 -0.4468 0.02048 0.01061 -0.0125 0.9625 0.2111
-3.750 -0.4186 0.01988 0.01033 -0.0132 0.9595 0.2688
-3.500 -0.3914 0.01912 0.01011 -0.0138 0.9568 0.3689
-3.250 -0.3734 0.01844 0.01003 -0.0120 0.9518 0.4889
-3.000 -0.3484 0.01814 0.01017 -0.0112 0.9478 0.5925
-2.750 -0.3187 0.01811 0.01035 -0.0112 0.9445 0.6621
-2.500 -0.2895 0.01818 0.01048 -0.0112 0.9412 0.7088
-2.250 -0.2672 0.01820 0.01053 -0.0098 0.9354 0.7424
-2.000 -0.2379 0.01829 0.01063 -0.0097 0.9313 0.7730
-1.750 -0.2043 0.01844 0.01081 -0.0104 0.9283 0.8002
-1.500 -0.1781 0.01859 0.01097 -0.0096 0.9234 0.8256
-1.250 -0.1504 0.01881 0.01122 -0.0089 0.9182 0.8542
-1.000 -0.1139 0.01915 0.01157 -0.0098 0.9150 0.8807
-0.750 -0.0728 0.01939 0.01178 -0.0121 0.9125 0.8974
-0.500 -0.0417 0.01951 0.01186 -0.0128 0.9072 0.9098
-0.250 -0.0043 0.01965 0.01197 -0.0149 0.9023 0.9187
0.000 0.0357 0.01973 0.01202 -0.0174 0.8986 0.9276
0.250 0.0812 0.01980 0.01208 -0.0211 0.8961 0.9343
0.500 0.1125 0.01990 0.01218 -0.0221 0.8890 0.9440
0.750 0.1543 0.01995 0.01223 -0.0252 0.8844 0.9507
1.000 0.1984 0.01992 0.01222 -0.0286 0.8810 0.9571
1.250 0.2411 0.01994 0.01228 -0.0319 0.8756 0.9622
1.500 0.2787 0.01991 0.01230 -0.0341 0.8687 0.9697
1.750 0.3280 0.01972 0.01217 -0.0384 0.8649 0.9729
2.000 0.3688 0.01942 0.01194 -0.0409 0.8539 0.9782
2.250 0.4138 0.01866 0.01123 -0.0433 0.8386 0.9821
2.500 0.4568 0.01795 0.01058 -0.0455 0.8199 0.9858
2.750 0.4971 0.01746 0.01017 -0.0475 0.8013 0.9910
3.000 0.5357 0.01707 0.00986 -0.0493 0.7783 0.9962
3.250 0.5754 0.01661 0.00944 -0.0512 0.7492 1.0000
3.500 0.6060 0.01617 0.00895 -0.0510 0.7115 1.0000
3.750 0.6435 0.01581 0.00839 -0.0520 0.6524 1.0000
4.000 0.6684 0.01590 0.00812 -0.0508 0.5706 1.0000
4.250 0.6809 0.01640 0.00810 -0.0477 0.4731 1.0000
4.500 0.6861 0.01717 0.00832 -0.0435 0.3782 1.0000
4.750 0.6911 0.01796 0.00866 -0.0394 0.3040 1.0000
5.000 0.6984 0.01867 0.00904 -0.0358 0.2512 1.0000
5.250 0.7079 0.01930 0.00944 -0.0326 0.2134 1.0000
5.500 0.7180 0.01990 0.00987 -0.0296 0.1855 1.0000
5.750 0.7296 0.02045 0.01031 -0.0267 0.1641 1.0000
6.000 0.7414 0.02102 0.01079 -0.0239 0.1473 1.0000
6.250 0.7535 0.02159 0.01129 -0.0211 0.1341 1.0000
6.500 0.7654 0.02221 0.01183 -0.0183 0.1231 1.0000
6.750 0.7787 0.02278 0.01240 -0.0158 0.1133 1.0000
7.000 0.7918 0.02342 0.01301 -0.0133 0.1053 1.0000
7.250 0.8051 0.02408 0.01363 -0.0109 0.0983 1.0000
7.500 0.8193 0.02477 0.01435 -0.0086 0.0921 1.0000
7.750 0.8333 0.02546 0.01503 -0.0064 0.0866 1.0000
8.000 0.8482 0.02626 0.01584 -0.0043 0.0818 1.0000
8.250 0.8642 0.02702 0.01665 -0.0025 0.0771 1.0000
8.500 0.8788 0.02791 0.01748 -0.0006 0.0734 1.0000
8.750 0.8973 0.02879 0.01849 0.0008 0.0694 1.0000
9.000 0.9140 0.02967 0.01941 0.0023 0.0660 1.0000
9.250 0.9301 0.03069 0.02036 0.0038 0.0632 1.0000
9.500 0.9490 0.03175 0.02164 0.0050 0.0600 1.0000
9.750 0.9658 0.03280 0.02278 0.0064 0.0573 1.0000
10.000 0.9811 0.03384 0.02379 0.0079 0.0552 1.0000
10.250 0.9981 0.03517 0.02529 0.0092 0.0528 1.0000
10.500 1.0139 0.03655 0.02688 0.0106 0.0507 1.0000
10.750 1.0275 0.03782 0.02825 0.0122 0.0490 1.0000
11.000 1.0404 0.03902 0.02946 0.0138 0.0475 1.0000
11.250 1.0517 0.04067 0.03130 0.0155 0.0460 1.0000
11.750 1.0658 0.04438 0.03555 0.0198 0.0432 1.0000
12.000 1.0711 0.04625 0.03761 0.0219 0.0423 1.0000
12.250 1.0756 0.04806 0.03955 0.0239 0.0415 1.0000
12.500 1.0800 0.04983 0.04141 0.0257 0.0408 1.0000
12.750 1.0808 0.05204 0.04376 0.0276 0.0401 1.0000
13.000 1.0678 0.05528 0.04740 0.0303 0.0395 1.0000
13.250 1.0524 0.05884 0.05129 0.0324 0.0389 1.0000
13.500 1.0347 0.06279 0.05555 0.0338 0.0385 1.0000
13.750 1.0139 0.06732 0.06038 0.0343 0.0381 1.0000
14.000 0.9890 0.07277 0.06610 0.0338 0.0380 1.0000
14.250 0.9579 0.07972 0.07333 0.0315 0.0380 1.0000
14.500 0.9169 0.08944 0.08333 0.0264 0.0384 1.0000
14.750 0.8581 0.10533 0.09948 0.0161 0.0392 1.0000
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