LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Reynolds number: 200,000 Max Cl/Cd: 65.36 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l188root-il-200000-n5.txt Download as CSV file: xf-l188root-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7752 0.06699 0.06237 -0.0692 1.0000 0.0262
-13.500 -0.8137 0.05768 0.05274 -0.0756 1.0000 0.0261
-13.250 -0.8375 0.05179 0.04659 -0.0787 1.0000 0.0262
-13.000 -0.8548 0.04737 0.04193 -0.0799 1.0000 0.0264
-12.750 -0.8683 0.04387 0.03817 -0.0799 1.0000 0.0266
-12.500 -0.8799 0.04107 0.03514 -0.0787 1.0000 0.0269
-12.250 -0.8930 0.03899 0.03285 -0.0756 1.0000 0.0271
-12.000 -0.9129 0.03779 0.03149 -0.0699 1.0000 0.0273
-11.750 -0.9304 0.03666 0.03018 -0.0640 0.9997 0.0276
-11.500 -0.9099 0.03508 0.02852 -0.0650 0.9953 0.0281
-11.250 -0.8879 0.03388 0.02726 -0.0659 0.9913 0.0287
-11.000 -0.8658 0.03260 0.02584 -0.0667 0.9871 0.0295
-10.750 -0.8417 0.03111 0.02414 -0.0678 0.9839 0.0304
-10.500 -0.8194 0.02958 0.02235 -0.0683 0.9799 0.0313
-10.250 -0.7957 0.02815 0.02068 -0.0688 0.9758 0.0321
-10.000 -0.7688 0.02712 0.01963 -0.0699 0.9726 0.0329
-9.750 -0.7408 0.02622 0.01866 -0.0709 0.9699 0.0339
-9.500 -0.7180 0.02538 0.01771 -0.0708 0.9644 0.0352
-9.250 -0.6914 0.02443 0.01656 -0.0713 0.9605 0.0366
-9.000 -0.6634 0.02354 0.01563 -0.0721 0.9575 0.0378
-8.750 -0.6391 0.02285 0.01491 -0.0721 0.9528 0.0390
-8.500 -0.6147 0.02215 0.01413 -0.0720 0.9477 0.0405
-8.250 -0.5873 0.02145 0.01329 -0.0723 0.9439 0.0423
-8.000 -0.5601 0.02076 0.01262 -0.0728 0.9406 0.0441
-7.750 -0.5388 0.02027 0.01208 -0.0719 0.9342 0.0459
-7.500 -0.5135 0.01970 0.01142 -0.0717 0.9295 0.0480
-7.250 -0.4873 0.01909 0.01080 -0.0717 0.9257 0.0502
-7.000 -0.4642 0.01866 0.01035 -0.0711 0.9203 0.0528
-6.750 -0.4401 0.01822 0.00982 -0.0706 0.9148 0.0557
-6.500 -0.4151 0.01769 0.00931 -0.0703 0.9104 0.0586
-6.250 -0.3897 0.01728 0.00886 -0.0700 0.9062 0.0624
-6.000 -0.3671 0.01687 0.00845 -0.0692 0.8998 0.0662
-5.750 -0.3419 0.01649 0.00805 -0.0688 0.8949 0.0708
-5.500 -0.3161 0.01607 0.00762 -0.0685 0.8910 0.0761
-5.250 -0.2922 0.01577 0.00730 -0.0679 0.8850 0.0823
-5.000 -0.2676 0.01540 0.00697 -0.0674 0.8794 0.0896
-4.750 -0.2416 0.01505 0.00662 -0.0671 0.8750 0.0984
-4.500 -0.2163 0.01475 0.00632 -0.0667 0.8701 0.1093
-4.000 -0.1660 0.01410 0.00578 -0.0659 0.8590 0.1405
-3.750 -0.1400 0.01373 0.00549 -0.0657 0.8549 0.1646
-3.500 -0.1161 0.01340 0.00530 -0.0651 0.8481 0.1969
-3.250 -0.0914 0.01295 0.00504 -0.0647 0.8428 0.2449
-3.000 -0.0672 0.01235 0.00474 -0.0643 0.8386 0.3242
-2.750 -0.0475 0.01167 0.00465 -0.0631 0.8317 0.4562
-2.500 -0.0236 0.01136 0.00464 -0.0622 0.8262 0.5461
-2.250 0.0032 0.01121 0.00459 -0.0617 0.8219 0.5923
-2.000 0.0290 0.01118 0.00462 -0.0612 0.8153 0.6232
-1.750 0.0558 0.01113 0.00460 -0.0608 0.8098 0.6477
-1.500 0.0838 0.01108 0.00454 -0.0605 0.8055 0.6684
-1.250 0.1102 0.01109 0.00457 -0.0601 0.7993 0.6875
-1.000 0.1371 0.01109 0.00458 -0.0597 0.7935 0.7074
-0.750 0.1642 0.01107 0.00460 -0.0592 0.7891 0.7298
-0.500 0.1898 0.01111 0.00470 -0.0584 0.7832 0.7511
-0.250 0.2168 0.01112 0.00471 -0.0581 0.7773 0.7647
0.000 0.2453 0.01107 0.00464 -0.0580 0.7727 0.7716
0.250 0.2731 0.01109 0.00463 -0.0580 0.7669 0.7793
0.500 0.3007 0.01108 0.00464 -0.0579 0.7612 0.7856
0.750 0.3292 0.01106 0.00460 -0.0579 0.7564 0.7932
1.000 0.3569 0.01108 0.00463 -0.0578 0.7508 0.8006
1.250 0.3841 0.01109 0.00468 -0.0576 0.7450 0.8080
1.500 0.4125 0.01110 0.00468 -0.0577 0.7401 0.8162
1.750 0.4400 0.01112 0.00474 -0.0575 0.7348 0.8241
2.000 0.4669 0.01115 0.00480 -0.0572 0.7273 0.8333
2.250 0.4933 0.01108 0.00474 -0.0566 0.7139 0.8419
2.500 0.5190 0.01102 0.00464 -0.0558 0.6956 0.8522
2.750 0.5450 0.01100 0.00461 -0.0551 0.6796 0.8632
3.000 0.5719 0.01102 0.00464 -0.0547 0.6670 0.8749
3.250 0.5990 0.01107 0.00468 -0.0543 0.6540 0.8881
3.500 0.6267 0.01112 0.00477 -0.0542 0.6394 0.9031
3.750 0.6560 0.01120 0.00486 -0.0543 0.6231 0.9193
4.000 0.6871 0.01131 0.00495 -0.0549 0.6040 0.9362
4.250 0.7192 0.01145 0.00506 -0.0558 0.5801 0.9541
4.500 0.7519 0.01165 0.00518 -0.0569 0.5480 0.9722
4.750 0.7830 0.01198 0.00532 -0.0579 0.4996 0.9915
5.000 0.8003 0.01258 0.00554 -0.0562 0.4256 1.0000
5.250 0.8071 0.01341 0.00594 -0.0526 0.3554 1.0000
5.500 0.8175 0.01420 0.00641 -0.0497 0.3015 1.0000
5.750 0.8306 0.01490 0.00688 -0.0474 0.2593 1.0000
6.000 0.8454 0.01555 0.00734 -0.0454 0.2265 1.0000
6.250 0.8611 0.01616 0.00781 -0.0435 0.2002 1.0000
6.500 0.8776 0.01674 0.00827 -0.0418 0.1788 1.0000
6.750 0.8940 0.01731 0.00874 -0.0401 0.1611 1.0000
7.000 0.9096 0.01785 0.00922 -0.0382 0.1468 1.0000
7.250 0.9253 0.01840 0.00973 -0.0364 0.1347 1.0000
7.500 0.9411 0.01899 0.01027 -0.0347 0.1243 1.0000
7.750 0.9570 0.01961 0.01084 -0.0330 0.1151 1.0000
8.000 0.9739 0.02019 0.01143 -0.0316 0.1071 1.0000
8.250 0.9894 0.02088 0.01208 -0.0300 0.1002 1.0000
8.500 1.0063 0.02151 0.01273 -0.0286 0.0939 1.0000
8.750 1.0214 0.02226 0.01345 -0.0271 0.0886 1.0000
9.000 1.0382 0.02293 0.01416 -0.0258 0.0835 1.0000
9.250 1.0528 0.02374 0.01496 -0.0244 0.0792 1.0000
9.500 1.0687 0.02449 0.01576 -0.0231 0.0753 1.0000
9.750 1.0839 0.02530 0.01659 -0.0218 0.0716 1.0000
10.000 1.0970 0.02627 0.01754 -0.0203 0.0685 1.0000
10.250 1.1125 0.02709 0.01844 -0.0191 0.0655 1.0000
10.500 1.1269 0.02799 0.01939 -0.0178 0.0626 1.0000
10.750 1.1388 0.02908 0.02047 -0.0165 0.0603 1.0000
11.000 1.1529 0.03005 0.02153 -0.0152 0.0580 1.0000
11.250 1.1664 0.03107 0.02262 -0.0140 0.0557 1.0000
11.500 1.1786 0.03219 0.02377 -0.0128 0.0538 1.0000
11.750 1.1889 0.03348 0.02507 -0.0115 0.0521 1.0000
12.000 1.2017 0.03461 0.02631 -0.0104 0.0503 1.0000
12.250 1.2134 0.03584 0.02762 -0.0093 0.0486 1.0000
12.500 1.2241 0.03715 0.02899 -0.0083 0.0472 1.0000
12.750 1.2328 0.03863 0.03049 -0.0071 0.0459 1.0000
13.000 1.2424 0.04010 0.03205 -0.0061 0.0446 1.0000
13.250 1.2523 0.04156 0.03363 -0.0051 0.0433 1.0000
13.500 1.2611 0.04312 0.03529 -0.0042 0.0420 1.0000
13.750 1.2689 0.04479 0.03703 -0.0033 0.0410 1.0000
14.000 1.2754 0.04658 0.03887 -0.0025 0.0402 1.0000
14.250 1.2808 0.04853 0.04087 -0.0017 0.0394 1.0000
14.500 1.2874 0.05044 0.04295 -0.0009 0.0384 1.0000
14.750 1.2930 0.05248 0.04512 -0.0003 0.0375 1.0000
15.000 1.2975 0.05465 0.04741 0.0002 0.0366 1.0000
15.250 1.3011 0.05694 0.04980 0.0006 0.0358 1.0000
15.500 1.3041 0.05937 0.05232 0.0008 0.0351 1.0000
15.750 1.3060 0.06195 0.05496 0.0010 0.0346 1.0000
16.000 1.3070 0.06469 0.05778 0.0011 0.0341 1.0000
16.250 1.3067 0.06774 0.06103 0.0010 0.0335 1.0000
16.500 1.3052 0.07101 0.06448 0.0008 0.0329 1.0000
16.750 1.3027 0.07450 0.06814 0.0003 0.0323 1.0000
17.000 1.2991 0.07821 0.07199 -0.0005 0.0318 1.0000
17.250 1.2948 0.08210 0.07603 -0.0014 0.0313 1.0000
17.500 1.2898 0.08620 0.08027 -0.0027 0.0309 1.0000
17.750 1.2846 0.09046 0.08464 -0.0042 0.0305 1.0000
18.000 1.2791 0.09483 0.08911 -0.0058 0.0301 1.0000
18.250 1.2734 0.09927 0.09363 -0.0076 0.0298 1.0000
18.500 1.2664 0.10405 0.09850 -0.0096 0.0295 1.0000
18.750 1.2504 0.11079 0.10549 -0.0130 0.0292 1.0000
19.000 1.2325 0.11820 0.11314 -0.0170 0.0289 1.0000
19.250 1.2112 0.12656 0.12173 -0.0218 0.0287 1.0000
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Polar data table (+)
Polar graphs
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