LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 500,000 Max Cl/Cd: 108.98 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188tip-il-500000.txt Download as CSV file: xf-l188tip-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED L-188 TIP 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3061 0.10335 0.10108 -0.0531 0.9945 0.0319
-11.000 -0.3295 0.09291 0.09066 -0.0599 0.9936 0.0337
-10.750 -0.7210 0.03755 0.03385 -0.0886 0.9851 0.0200
-10.500 -0.7144 0.03335 0.02929 -0.0898 0.9817 0.0203
-10.250 -0.6976 0.03136 0.02713 -0.0902 0.9780 0.0206
-10.000 -0.6741 0.02972 0.02535 -0.0914 0.9758 0.0211
-9.750 -0.6483 0.02802 0.02346 -0.0928 0.9742 0.0216
-9.500 -0.6233 0.02597 0.02113 -0.0940 0.9726 0.0222
-9.250 -0.5973 0.02401 0.01884 -0.0951 0.9712 0.0228
-9.000 -0.5809 0.02284 0.01741 -0.0935 0.9660 0.0235
-8.750 -0.5573 0.02127 0.01557 -0.0936 0.9630 0.0242
-8.500 -0.5303 0.02021 0.01449 -0.0942 0.9608 0.0250
-8.250 -0.5019 0.01946 0.01366 -0.0948 0.9589 0.0258
-8.000 -0.4735 0.01864 0.01273 -0.0954 0.9571 0.0267
-7.750 -0.4534 0.01799 0.01196 -0.0940 0.9523 0.0276
-7.500 -0.4280 0.01741 0.01123 -0.0937 0.9488 0.0283
-7.250 -0.4037 0.01628 0.01006 -0.0934 0.9460 0.0296
-7.000 -0.3765 0.01583 0.00960 -0.0935 0.9436 0.0309
-6.750 -0.3510 0.01539 0.00910 -0.0932 0.9406 0.0323
-6.500 -0.3274 0.01498 0.00861 -0.0924 0.9362 0.0335
-6.250 -0.3041 0.01418 0.00779 -0.0917 0.9325 0.0351
-6.000 -0.2780 0.01377 0.00738 -0.0914 0.9296 0.0369
-5.750 -0.2511 0.01346 0.00702 -0.0912 0.9270 0.0392
-5.500 -0.2277 0.01295 0.00649 -0.0905 0.9228 0.0416
-5.250 -0.2028 0.01261 0.00616 -0.0900 0.9186 0.0442
-5.000 -0.1764 0.01233 0.00583 -0.0896 0.9151 0.0471
-4.750 -0.1507 0.01186 0.00537 -0.0892 0.9122 0.0514
-4.500 -0.1241 0.01166 0.00515 -0.0889 0.9088 0.0557
-4.250 -0.0994 0.01129 0.00481 -0.0884 0.9040 0.0616
-4.000 -0.0730 0.01102 0.00452 -0.0881 0.9001 0.0685
-3.750 -0.0459 0.01074 0.00426 -0.0878 0.8969 0.0776
-3.500 -0.0190 0.01046 0.00401 -0.0876 0.8937 0.0907
-3.250 0.0064 0.01017 0.00382 -0.0872 0.8886 0.1105
-3.000 0.0328 0.00985 0.00362 -0.0870 0.8843 0.1410
-2.750 0.0593 0.00945 0.00341 -0.0868 0.8807 0.1934
-2.500 0.0847 0.00895 0.00323 -0.0866 0.8770 0.2870
-2.250 0.1069 0.00818 0.00309 -0.0859 0.8713 0.4580
-2.000 0.1316 0.00776 0.00303 -0.0853 0.8669 0.5769
-1.750 0.1585 0.00756 0.00297 -0.0849 0.8634 0.6342
-1.500 0.1848 0.00747 0.00298 -0.0844 0.8582 0.6719
-1.250 0.2118 0.00738 0.00295 -0.0841 0.8530 0.7005
-1.000 0.2397 0.00731 0.00289 -0.0839 0.8488 0.7245
-0.750 0.2672 0.00727 0.00287 -0.0836 0.8440 0.7445
-0.500 0.2942 0.00722 0.00285 -0.0833 0.8381 0.7625
-0.250 0.3220 0.00714 0.00279 -0.0831 0.8333 0.7794
0.000 0.3492 0.00709 0.00277 -0.0828 0.8280 0.7974
0.250 0.3752 0.00700 0.00276 -0.0822 0.8217 0.8211
0.500 0.4010 0.00686 0.00271 -0.0814 0.8167 0.8505
0.750 0.4268 0.00679 0.00272 -0.0807 0.8101 0.8741
1.000 0.4540 0.00672 0.00270 -0.0804 0.8039 0.8935
1.250 0.4820 0.00664 0.00266 -0.0801 0.7949 0.9173
1.500 0.5140 0.00656 0.00256 -0.0806 0.7803 0.9427
1.750 0.5510 0.00655 0.00250 -0.0824 0.7651 0.9633
2.000 0.5893 0.00660 0.00248 -0.0847 0.7534 0.9796
2.250 0.6290 0.00665 0.00251 -0.0873 0.7405 0.9917
2.500 0.6703 0.00671 0.00253 -0.0903 0.7269 0.9999
2.750 0.6940 0.00678 0.00255 -0.0896 0.7136 1.0000
3.000 0.7178 0.00687 0.00259 -0.0887 0.6993 1.0000
3.250 0.7416 0.00698 0.00265 -0.0879 0.6840 1.0000
3.500 0.7651 0.00711 0.00271 -0.0869 0.6666 1.0000
3.750 0.7881 0.00726 0.00280 -0.0859 0.6470 1.0000
4.000 0.8108 0.00744 0.00290 -0.0848 0.6246 1.0000
4.250 0.8324 0.00768 0.00302 -0.0835 0.5965 1.0000
4.500 0.8530 0.00796 0.00319 -0.0821 0.5608 1.0000
4.750 0.8711 0.00839 0.00339 -0.0802 0.5107 1.0000
5.000 0.8845 0.00909 0.00372 -0.0775 0.4343 1.0000
5.250 0.8955 0.01002 0.00419 -0.0745 0.3480 1.0000
5.500 0.9098 0.01083 0.00466 -0.0722 0.2822 1.0000
5.750 0.9262 0.01153 0.00508 -0.0704 0.2322 1.0000
6.000 0.9443 0.01212 0.00548 -0.0688 0.1940 1.0000
6.250 0.9630 0.01267 0.00587 -0.0673 0.1649 1.0000
6.500 0.9818 0.01321 0.00628 -0.0659 0.1418 1.0000
6.750 1.0015 0.01368 0.00667 -0.0646 0.1243 1.0000
7.000 1.0207 0.01416 0.00708 -0.0632 0.1099 1.0000
7.250 1.0389 0.01465 0.00751 -0.0616 0.0984 1.0000
7.500 1.0561 0.01516 0.00796 -0.0599 0.0887 1.0000
7.750 1.0749 0.01559 0.00840 -0.0584 0.0814 1.0000
8.000 1.0916 0.01617 0.00893 -0.0567 0.0746 1.0000
8.250 1.1103 0.01663 0.00941 -0.0553 0.0693 1.0000
8.500 1.1260 0.01730 0.01005 -0.0534 0.0641 1.0000
8.750 1.1450 0.01776 0.01055 -0.0522 0.0602 1.0000
9.000 1.1603 0.01847 0.01123 -0.0504 0.0561 1.0000
9.250 1.1772 0.01908 0.01190 -0.0489 0.0532 1.0000
9.500 1.1947 0.01966 0.01251 -0.0475 0.0504 1.0000
9.750 1.2087 0.02047 0.01331 -0.0457 0.0476 1.0000
10.000 1.2235 0.02125 0.01414 -0.0440 0.0454 1.0000
10.250 1.2404 0.02188 0.01483 -0.0427 0.0433 1.0000
10.500 1.2558 0.02263 0.01560 -0.0412 0.0414 1.0000
10.750 1.2647 0.02386 0.01683 -0.0389 0.0395 1.0000
11.000 1.2798 0.02465 0.01770 -0.0375 0.0382 1.0000
11.250 1.2951 0.02542 0.01855 -0.0361 0.0367 1.0000
11.500 1.3094 0.02628 0.01944 -0.0347 0.0353 1.0000
11.750 1.3209 0.02734 0.02053 -0.0331 0.0340 1.0000
12.000 1.3264 0.02895 0.02218 -0.0308 0.0328 1.0000
12.250 1.3404 0.02988 0.02321 -0.0295 0.0320 1.0000
12.500 1.3525 0.03095 0.02437 -0.0281 0.0310 1.0000
12.750 1.3642 0.03206 0.02555 -0.0267 0.0300 1.0000
13.000 1.3749 0.03325 0.02679 -0.0254 0.0291 1.0000
13.250 1.3828 0.03472 0.02829 -0.0238 0.0283 1.0000
13.500 1.3853 0.03676 0.03039 -0.0218 0.0274 1.0000
13.750 1.3952 0.03810 0.03186 -0.0206 0.0269 1.0000
14.000 1.4034 0.03963 0.03351 -0.0193 0.0263 1.0000
14.250 1.4106 0.04126 0.03525 -0.0181 0.0257 1.0000
14.500 1.4169 0.04300 0.03708 -0.0170 0.0251 1.0000
14.750 1.4226 0.04482 0.03898 -0.0159 0.0246 1.0000
15.000 1.4274 0.04676 0.04099 -0.0150 0.0241 1.0000
15.250 1.4303 0.04895 0.04323 -0.0141 0.0236 1.0000
15.500 1.4280 0.05178 0.04614 -0.0128 0.0230 1.0000
15.750 1.4292 0.05432 0.04883 -0.0121 0.0226 1.0000
16.000 1.4306 0.05691 0.05158 -0.0117 0.0223 1.0000
16.250 1.4304 0.05975 0.05456 -0.0114 0.0219 1.0000
16.500 1.4289 0.06283 0.05778 -0.0113 0.0216 1.0000
16.750 1.4264 0.06613 0.06122 -0.0114 0.0212 1.0000
17.000 1.4232 0.06964 0.06487 -0.0117 0.0209 1.0000
17.250 1.4190 0.07337 0.06872 -0.0122 0.0206 1.0000
17.500 1.4140 0.07729 0.07275 -0.0130 0.0203 1.0000
17.750 1.4084 0.08142 0.07700 -0.0141 0.0201 1.0000
18.000 1.4019 0.08579 0.08148 -0.0153 0.0199 1.0000
18.250 1.3945 0.09043 0.08622 -0.0168 0.0197 1.0000
18.500 1.3856 0.09535 0.09125 -0.0186 0.0195 1.0000
18.750 1.3744 0.10073 0.09675 -0.0206 0.0193 1.0000
19.000 1.3592 0.10692 0.10309 -0.0232 0.0191 1.0000
19.250 1.3389 0.11429 0.11063 -0.0266 0.0189 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED L-188 TIP AIRFOIL (l188tip-il)