LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Reynolds number: 100,000 Max Cl/Cd: 51.11 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188root-il-100000.txt Download as CSV file: xf-l188root-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED L-188 ROOT 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4185 0.10221 0.09689 -0.0424 1.0000 0.1606
-9.750 -0.4355 0.09904 0.09381 -0.0437 1.0000 0.1672
-9.500 -0.5268 0.09515 0.09021 -0.0477 1.0000 0.1695
-9.250 -0.4578 0.09242 0.08736 -0.0422 1.0000 0.1736
-9.000 -0.4576 0.09032 0.08530 -0.0398 1.0000 0.1772
-8.750 -0.4810 0.08786 0.08294 -0.0380 1.0000 0.1815
-8.500 -0.5559 0.08510 0.08039 -0.0364 1.0000 0.1846
-8.250 -0.7404 0.05938 0.05340 -0.0365 1.0000 0.0947
-8.000 -0.7394 0.05585 0.04977 -0.0344 1.0000 0.0937
-7.750 -0.7398 0.05222 0.04594 -0.0322 1.0000 0.0924
-7.500 -0.7395 0.04830 0.04167 -0.0300 1.0000 0.0906
-7.250 -0.7356 0.04449 0.03742 -0.0279 1.0000 0.0894
-7.000 -0.7262 0.04167 0.03421 -0.0262 1.0000 0.0901
-6.750 -0.7136 0.03926 0.03139 -0.0247 1.0000 0.0919
-6.500 -0.6984 0.03698 0.02864 -0.0233 1.0000 0.0934
-6.250 -0.6809 0.03504 0.02621 -0.0221 1.0000 0.0949
-6.000 -0.6622 0.03310 0.02413 -0.0214 1.0000 0.0978
-5.750 -0.6392 0.03203 0.02302 -0.0213 0.9991 0.1017
-5.500 -0.6018 0.03067 0.02129 -0.0235 0.9950 0.1065
-5.250 -0.5662 0.02931 0.01982 -0.0256 0.9906 0.1124
-5.000 -0.5296 0.02846 0.01883 -0.0277 0.9859 0.1196
-4.750 -0.4923 0.02748 0.01786 -0.0300 0.9820 0.1282
-4.500 -0.4602 0.02691 0.01711 -0.0311 0.9764 0.1379
-4.250 -0.4232 0.02610 0.01644 -0.0334 0.9721 0.1512
-4.000 -0.3908 0.02543 0.01588 -0.0348 0.9670 0.1669
-3.750 -0.3597 0.02477 0.01537 -0.0359 0.9617 0.1878
-3.500 -0.3237 0.02407 0.01496 -0.0380 0.9577 0.2229
-3.250 -0.2964 0.02306 0.01452 -0.0388 0.9524 0.2924
-3.000 -0.2763 0.02168 0.01494 -0.0373 0.9472 0.6101
-2.750 -0.2466 0.02227 0.01566 -0.0364 0.9422 0.7032
-2.500 -0.2284 0.02272 0.01610 -0.0340 0.9354 0.7452
-2.250 -0.2046 0.02314 0.01651 -0.0324 0.9292 0.7797
-2.000 -0.1739 0.02361 0.01696 -0.0317 0.9248 0.8101
-1.750 -0.1635 0.02382 0.01716 -0.0281 0.9171 0.8339
-1.500 -0.1404 0.02413 0.01746 -0.0262 0.9116 0.8580
-1.250 -0.1078 0.02453 0.01779 -0.0262 0.9077 0.8833
-1.000 -0.0971 0.02475 0.01800 -0.0228 0.8995 0.9056
-0.750 -0.0581 0.02528 0.01848 -0.0240 0.8953 0.9331
-0.500 0.0319 0.02635 0.01944 -0.0347 0.8946 0.9629
-0.250 0.1043 0.02674 0.01972 -0.0439 0.8924 0.9725
0.000 0.1582 0.02698 0.01989 -0.0499 0.8886 0.9795
0.250 0.1977 0.02730 0.02018 -0.0539 0.8820 0.9887
0.500 0.2512 0.02746 0.02030 -0.0599 0.8778 0.9956
0.750 0.3061 0.02752 0.02033 -0.0660 0.8746 1.0000
1.000 0.2820 0.02784 0.02064 -0.0587 0.8626 1.0000
1.250 0.3095 0.02786 0.02064 -0.0597 0.8574 1.0000
1.500 0.2798 0.02807 0.02082 -0.0513 0.8450 1.0000
1.750 0.3142 0.02811 0.02083 -0.0531 0.8399 1.0000
2.000 0.3122 0.02853 0.02119 -0.0491 0.8287 1.0000
2.250 0.3543 0.02859 0.02124 -0.0518 0.8233 1.0000
2.500 0.3673 0.02907 0.02169 -0.0501 0.8127 1.0000
2.750 0.4149 0.02885 0.02149 -0.0532 0.8066 1.0000
3.000 0.4340 0.02912 0.02175 -0.0520 0.7946 1.0000
3.250 0.5037 0.02785 0.02055 -0.0574 0.7888 1.0000
3.500 0.5244 0.02782 0.02053 -0.0559 0.7754 1.0000
3.750 0.5641 0.02714 0.01991 -0.0568 0.7649 1.0000
4.000 0.6193 0.02556 0.01841 -0.0593 0.7575 1.0000
4.250 0.6486 0.02504 0.01794 -0.0586 0.7457 1.0000
4.500 0.7067 0.02306 0.01604 -0.0611 0.7390 1.0000
4.750 0.7338 0.02247 0.01552 -0.0598 0.7252 1.0000
5.000 0.7674 0.02154 0.01465 -0.0593 0.7115 1.0000
5.250 0.8027 0.02050 0.01367 -0.0588 0.6961 1.0000
5.500 0.8346 0.01960 0.01282 -0.0580 0.6773 1.0000
5.750 0.8666 0.01871 0.01194 -0.0571 0.6545 1.0000
6.000 0.8864 0.01834 0.01161 -0.0545 0.6241 1.0000
6.250 0.9060 0.01800 0.01121 -0.0519 0.5823 1.0000
6.500 0.9184 0.01797 0.01097 -0.0481 0.5124 1.0000
6.750 0.9203 0.01879 0.01097 -0.0429 0.3954 1.0000
7.000 0.9180 0.02035 0.01179 -0.0379 0.3203 1.0000
7.250 0.9228 0.02176 0.01277 -0.0344 0.2735 1.0000
7.500 0.9323 0.02300 0.01370 -0.0316 0.2416 1.0000
7.750 0.9461 0.02422 0.01465 -0.0296 0.2179 1.0000
8.000 0.9629 0.02534 0.01563 -0.0280 0.1981 1.0000
8.250 0.9826 0.02650 0.01667 -0.0270 0.1821 1.0000
8.500 1.0047 0.02770 0.01775 -0.0264 0.1685 1.0000
8.750 1.0316 0.02905 0.01892 -0.0266 0.1565 1.0000
9.000 1.0513 0.03008 0.02006 -0.0255 0.1467 1.0000
9.250 1.0784 0.03153 0.02149 -0.0257 0.1379 1.0000
9.500 1.1027 0.03278 0.02268 -0.0255 0.1301 1.0000
9.750 1.1286 0.03441 0.02443 -0.0255 0.1235 1.0000
10.000 1.1502 0.03572 0.02579 -0.0248 0.1175 1.0000
10.250 1.1778 0.03771 0.02780 -0.0252 0.1123 1.0000
10.500 1.1946 0.03929 0.02965 -0.0238 0.1079 1.0000
10.750 1.2149 0.04080 0.03120 -0.0232 0.1036 1.0000
11.000 1.2371 0.04327 0.03376 -0.0230 0.1001 1.0000
11.250 1.2441 0.04528 0.03618 -0.0204 0.0975 1.0000
11.500 1.2536 0.04730 0.03847 -0.0183 0.0947 1.0000
11.750 1.2703 0.04910 0.04031 -0.0174 0.0918 1.0000
12.000 1.2915 0.05240 0.04360 -0.0177 0.0892 1.0000
12.250 1.2824 0.05484 0.04649 -0.0135 0.0883 1.0000
12.500 1.2691 0.05747 0.04951 -0.0090 0.0875 1.0000
12.750 1.2529 0.06043 0.05281 -0.0049 0.0868 1.0000
13.000 1.2337 0.06373 0.05643 -0.0013 0.0862 1.0000
13.250 1.2112 0.06746 0.06045 0.0017 0.0858 1.0000
13.500 1.1849 0.07175 0.06503 0.0041 0.0857 1.0000
13.750 1.1548 0.07678 0.07033 0.0055 0.0859 1.0000
14.000 1.1209 0.08274 0.07654 0.0058 0.0863 1.0000
14.250 1.0839 0.08977 0.08380 0.0046 0.0870 1.0000
14.500 1.0466 0.09790 0.09211 0.0020 0.0878 1.0000
14.750 1.0133 0.10677 0.10110 -0.0017 0.0886 1.0000
15.000 0.9891 0.11558 0.10998 -0.0054 0.0893 1.0000
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