LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Reynolds number: 500,000 Max Cl/Cd: 94.86 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188root-il-500000.txt Download as CSV file: xf-l188root-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.5166 0.17049 0.16787 -0.0133 1.0000 0.0287
-15.500 -0.8191 0.08575 0.08270 -0.0547 1.0000 0.0237
-15.250 -0.8672 0.07231 0.06903 -0.0644 1.0000 0.0235
-15.000 -0.9002 0.06309 0.05958 -0.0710 1.0000 0.0235
-14.750 -0.9251 0.05617 0.05244 -0.0755 1.0000 0.0235
-14.500 -0.9449 0.05066 0.04670 -0.0785 1.0000 0.0235
-14.250 -0.9597 0.04627 0.04209 -0.0803 1.0000 0.0236
-14.000 -0.9705 0.04275 0.03834 -0.0812 1.0000 0.0237
-13.750 -0.9815 0.03931 0.03469 -0.0811 1.0000 0.0239
-13.500 -0.9856 0.03653 0.03178 -0.0805 1.0000 0.0241
-13.250 -0.9833 0.03471 0.02988 -0.0794 1.0000 0.0244
-13.000 -0.9810 0.03335 0.02846 -0.0777 1.0000 0.0246
-12.750 -0.9925 0.03254 0.02760 -0.0728 1.0000 0.0248
-12.500 -1.0231 0.03232 0.02732 -0.0638 0.9999 0.0248
-12.250 -0.9995 0.03092 0.02582 -0.0652 0.9972 0.0252
-12.000 -0.9751 0.02951 0.02427 -0.0665 0.9947 0.0258
-11.750 -0.9511 0.02816 0.02277 -0.0676 0.9922 0.0263
-11.500 -0.9269 0.02692 0.02135 -0.0684 0.9890 0.0270
-11.250 -0.8996 0.02594 0.02014 -0.0696 0.9864 0.0276
-11.000 -0.8731 0.02415 0.01830 -0.0710 0.9848 0.0284
-10.750 -0.8420 0.02323 0.01735 -0.0727 0.9835 0.0291
-10.500 -0.8142 0.02242 0.01648 -0.0736 0.9806 0.0299
-10.250 -0.7870 0.02160 0.01557 -0.0743 0.9771 0.0307
-10.000 -0.7580 0.02082 0.01465 -0.0752 0.9743 0.0316
-9.750 -0.7296 0.01974 0.01348 -0.0761 0.9719 0.0325
-9.500 -0.7042 0.01903 0.01279 -0.0763 0.9680 0.0335
-9.250 -0.6798 0.01856 0.01229 -0.0760 0.9630 0.0346
-9.000 -0.6536 0.01803 0.01168 -0.0761 0.9591 0.0359
-8.750 -0.6284 0.01760 0.01115 -0.0758 0.9552 0.0369
-8.500 -0.6092 0.01674 0.01030 -0.0746 0.9492 0.0382
-8.250 -0.5856 0.01630 0.00985 -0.0740 0.9446 0.0395
-8.000 -0.5619 0.01591 0.00941 -0.0733 0.9405 0.0411
-7.750 -0.5384 0.01560 0.00902 -0.0726 0.9350 0.0425
-7.500 -0.5171 0.01494 0.00840 -0.0716 0.9298 0.0445
-7.250 -0.4933 0.01460 0.00803 -0.0709 0.9256 0.0465
-7.000 -0.4688 0.01432 0.00768 -0.0703 0.9206 0.0484
-6.750 -0.4463 0.01376 0.00714 -0.0695 0.9152 0.0510
-6.500 -0.4215 0.01346 0.00682 -0.0689 0.9107 0.0538
-6.250 -0.3971 0.01312 0.00644 -0.0683 0.9064 0.0567
-6.000 -0.3725 0.01275 0.00610 -0.0678 0.9009 0.0603
-5.750 -0.3465 0.01253 0.00583 -0.0674 0.8959 0.0639
-5.500 -0.3221 0.01211 0.00543 -0.0668 0.8916 0.0692
-5.250 -0.2962 0.01185 0.00516 -0.0664 0.8865 0.0745
-5.000 -0.2706 0.01154 0.00488 -0.0661 0.8811 0.0814
-4.750 -0.2447 0.01122 0.00458 -0.0657 0.8763 0.0898
-4.500 -0.2185 0.01096 0.00433 -0.0654 0.8718 0.1001
-4.250 -0.1923 0.01068 0.00411 -0.0652 0.8660 0.1136
-4.000 -0.1660 0.01039 0.00389 -0.0649 0.8608 0.1321
-3.750 -0.1397 0.01008 0.00365 -0.0647 0.8564 0.1582
-3.500 -0.1139 0.00973 0.00347 -0.0645 0.8505 0.1968
-3.250 -0.0885 0.00929 0.00326 -0.0642 0.8447 0.2566
-3.000 -0.0647 0.00863 0.00298 -0.0638 0.8400 0.3609
-2.750 -0.0424 0.00794 0.00286 -0.0630 0.8341 0.5095
-2.500 -0.0162 0.00772 0.00282 -0.0626 0.8281 0.5713
-2.250 0.0113 0.00761 0.00276 -0.0624 0.8231 0.6070
-2.000 0.0390 0.00757 0.00275 -0.0623 0.8174 0.6326
-1.750 0.0670 0.00753 0.00273 -0.0622 0.8114 0.6525
-1.500 0.0953 0.00750 0.00269 -0.0621 0.8063 0.6691
-1.250 0.1234 0.00748 0.00269 -0.0620 0.8003 0.6834
-1.000 0.1516 0.00747 0.00268 -0.0620 0.7943 0.6965
-0.750 0.1803 0.00748 0.00265 -0.0620 0.7892 0.7095
-0.500 0.2083 0.00749 0.00269 -0.0619 0.7832 0.7216
-0.250 0.2363 0.00749 0.00271 -0.0618 0.7771 0.7342
0.000 0.2644 0.00753 0.00273 -0.0617 0.7719 0.7492
0.250 0.2918 0.00756 0.00282 -0.0614 0.7659 0.7654
0.500 0.3198 0.00758 0.00286 -0.0613 0.7601 0.7762
0.750 0.3487 0.00761 0.00284 -0.0615 0.7549 0.7830
1.000 0.3767 0.00760 0.00288 -0.0615 0.7483 0.7900
1.250 0.4048 0.00761 0.00281 -0.0613 0.7383 0.7974
1.500 0.4315 0.00754 0.00276 -0.0609 0.7244 0.8042
1.750 0.4588 0.00754 0.00275 -0.0607 0.7124 0.8122
2.000 0.4863 0.00755 0.00274 -0.0605 0.7028 0.8200
2.250 0.5136 0.00755 0.00277 -0.0603 0.6928 0.8285
2.500 0.5410 0.00757 0.00280 -0.0601 0.6836 0.8370
2.750 0.5680 0.00758 0.00283 -0.0598 0.6734 0.8468
3.000 0.5947 0.00759 0.00289 -0.0595 0.6630 0.8571
3.500 0.6470 0.00765 0.00300 -0.0586 0.6393 0.8821
3.750 0.6725 0.00769 0.00308 -0.0580 0.6258 0.8976
4.000 0.6976 0.00775 0.00317 -0.0572 0.6101 0.9168
4.250 0.7240 0.00785 0.00327 -0.0568 0.5912 0.9392
4.500 0.7554 0.00803 0.00340 -0.0575 0.5660 0.9596
4.750 0.7892 0.00832 0.00356 -0.0590 0.5266 0.9775
5.000 0.8212 0.00893 0.00384 -0.0604 0.4519 0.9938
5.250 0.8382 0.00995 0.00432 -0.0591 0.3531 1.0000
5.500 0.8496 0.01068 0.00472 -0.0563 0.2930 1.0000
5.750 0.8647 0.01131 0.00510 -0.0542 0.2477 1.0000
6.000 0.8819 0.01187 0.00547 -0.0525 0.2124 1.0000
6.250 0.8999 0.01240 0.00583 -0.0509 0.1847 1.0000
6.500 0.9188 0.01288 0.00619 -0.0495 0.1626 1.0000
6.750 0.9376 0.01336 0.00657 -0.0481 0.1448 1.0000
7.000 0.9567 0.01382 0.00695 -0.0467 0.1304 1.0000
7.250 0.9759 0.01426 0.00733 -0.0454 0.1187 1.0000
7.500 0.9937 0.01470 0.00773 -0.0437 0.1091 1.0000
7.750 1.0098 0.01522 0.00819 -0.0419 0.1006 1.0000
8.000 1.0282 0.01565 0.00861 -0.0404 0.0939 1.0000
8.250 1.0449 0.01619 0.00913 -0.0388 0.0877 1.0000
8.500 1.0631 0.01668 0.00961 -0.0374 0.0823 1.0000
8.750 1.0791 0.01731 0.01021 -0.0358 0.0774 1.0000
9.000 1.0976 0.01780 0.01073 -0.0345 0.0733 1.0000
9.250 1.1119 0.01856 0.01145 -0.0328 0.0691 1.0000
9.500 1.1303 0.01909 0.01202 -0.0316 0.0660 1.0000
9.750 1.1473 0.01971 0.01264 -0.0303 0.0629 1.0000
10.000 1.1594 0.02066 0.01357 -0.0284 0.0599 1.0000
10.250 1.1776 0.02122 0.01420 -0.0274 0.0577 1.0000
10.500 1.1942 0.02190 0.01490 -0.0262 0.0553 1.0000
10.750 1.2063 0.02288 0.01587 -0.0245 0.0530 1.0000
11.000 1.2209 0.02373 0.01678 -0.0232 0.0512 1.0000
11.250 1.2364 0.02452 0.01761 -0.0220 0.0494 1.0000
11.500 1.2509 0.02538 0.01850 -0.0208 0.0478 1.0000
11.750 1.2612 0.02656 0.01968 -0.0192 0.0461 1.0000
12.000 1.2731 0.02766 0.02084 -0.0178 0.0448 1.0000
12.250 1.2874 0.02857 0.02183 -0.0167 0.0434 1.0000
12.500 1.3005 0.02960 0.02290 -0.0155 0.0421 1.0000
12.750 1.3120 0.03075 0.02408 -0.0143 0.0409 1.0000
13.000 1.3181 0.03236 0.02570 -0.0127 0.0398 1.0000
13.250 1.3285 0.03367 0.02709 -0.0115 0.0389 1.0000
13.500 1.3402 0.03488 0.02840 -0.0105 0.0380 1.0000
13.750 1.3507 0.03620 0.02978 -0.0095 0.0370 1.0000
14.000 1.3604 0.03759 0.03122 -0.0086 0.0360 1.0000
14.250 1.3684 0.03915 0.03282 -0.0076 0.0352 1.0000
14.500 1.3715 0.04118 0.03487 -0.0063 0.0344 1.0000
14.750 1.3785 0.04292 0.03671 -0.0054 0.0338 1.0000
15.000 1.3862 0.04463 0.03854 -0.0046 0.0332 1.0000
15.250 1.3928 0.04649 0.04050 -0.0039 0.0325 1.0000
15.500 1.3988 0.04845 0.04254 -0.0033 0.0319 1.0000
15.750 1.4043 0.05049 0.04465 -0.0028 0.0313 1.0000
16.000 1.4089 0.05265 0.04687 -0.0025 0.0307 1.0000
16.250 1.4116 0.05504 0.04930 -0.0021 0.0302 1.0000
16.500 1.4107 0.05777 0.05206 -0.0013 0.0295 1.0000
16.750 1.4132 0.06039 0.05483 -0.0013 0.0292 1.0000
17.000 1.4145 0.06318 0.05776 -0.0013 0.0287 1.0000
17.250 1.4145 0.06618 0.06089 -0.0015 0.0283 1.0000
17.500 1.4137 0.06935 0.06418 -0.0018 0.0279 1.0000
17.750 1.4122 0.07267 0.06762 -0.0023 0.0275 1.0000
18.000 1.4103 0.07613 0.07118 -0.0030 0.0271 1.0000
18.250 1.4077 0.07971 0.07486 -0.0038 0.0268 1.0000
18.500 1.4048 0.08341 0.07864 -0.0047 0.0265 1.0000
18.750 1.4014 0.08722 0.08253 -0.0058 0.0262 1.0000
19.000 1.3972 0.09117 0.08655 -0.0070 0.0259 1.0000
19.250 1.3912 0.09531 0.09076 -0.0081 0.0256 1.0000
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