NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Reynolds number: 200,000 Max Cl/Cd: 70.79 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lrn1015-il-200000.txt Download as CSV file: xf-lrn1015-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA LRN 1015 (NASA TM 102840)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0469 0.09429 0.08995 -0.1141 0.8423 0.0456
-10.500 -0.0487 0.09116 0.08682 -0.1162 0.8400 0.0471
-10.250 -0.0697 0.08665 0.08242 -0.1220 0.8371 0.0483
-10.000 -0.0837 0.08167 0.07751 -0.1270 0.8343 0.0484
-9.750 -0.0574 0.08012 0.07595 -0.1219 0.8331 0.0497
-9.500 -0.0467 0.07821 0.07406 -0.1212 0.8311 0.0509
-9.250 -0.0430 0.07570 0.07157 -0.1217 0.8289 0.0524
-9.000 -0.0459 0.07246 0.06835 -0.1233 0.8266 0.0541
-8.750 -0.0571 0.06827 0.06419 -0.1265 0.8239 0.0552
-8.500 -0.0739 0.06437 0.06033 -0.1289 0.8206 0.0555
-8.250 -0.0995 0.06176 0.05767 -0.1283 0.8172 0.0565
-8.000 -0.1370 0.06059 0.05605 -0.1262 0.8135 0.0580
-7.750 -0.1357 0.05583 0.05127 -0.1258 0.8114 0.0591
-7.500 -0.1193 0.05340 0.04895 -0.1254 0.8097 0.0605
-7.250 -0.1102 0.05174 0.04728 -0.1244 0.8073 0.0624
-7.000 -0.1055 0.05005 0.04549 -0.1232 0.8045 0.0659
-6.750 -0.1123 0.04792 0.04289 -0.1209 0.8012 0.0710
-6.500 -0.0953 0.04576 0.04086 -0.1205 0.7990 0.0734
-6.000 -0.0712 0.04230 0.03704 -0.1181 0.7947 0.0865
-5.750 -0.0535 0.04116 0.03579 -0.1171 0.7932 0.0930
-5.500 -0.0487 0.03981 0.03431 -0.1152 0.7893 0.1009
-5.250 -0.0340 0.03892 0.03339 -0.1138 0.7858 0.1076
-5.000 -0.0199 0.03743 0.03178 -0.1126 0.7830 0.1185
-4.750 0.0111 0.03214 0.02473 -0.1078 0.7810 0.0486
-4.500 0.0354 0.02942 0.02194 -0.1073 0.7796 0.0455
-4.250 0.0623 0.02807 0.02035 -0.1066 0.7783 0.0441
-4.000 0.0704 0.02818 0.02041 -0.1040 0.7730 0.0450
-3.750 0.0869 0.02789 0.02002 -0.1023 0.7694 0.0458
-3.500 0.1102 0.02721 0.01925 -0.1014 0.7670 0.0458
-3.250 0.1365 0.02650 0.01848 -0.1007 0.7651 0.0462
-3.000 0.1641 0.02589 0.01781 -0.1003 0.7635 0.0474
-2.750 0.1912 0.02524 0.01715 -0.0999 0.7623 0.0494
-2.500 0.1773 0.02645 0.01845 -0.0946 0.7535 0.0506
-2.250 0.1997 0.02623 0.01828 -0.0938 0.7508 0.0550
-2.000 0.2261 0.02586 0.01787 -0.0934 0.7491 0.0596
-1.750 0.2554 0.02545 0.01743 -0.0934 0.7476 0.0708
-1.500 0.2450 0.02666 0.01871 -0.0885 0.7393 0.0794
-1.250 0.2439 0.02464 0.01895 -0.0844 0.7353 0.6233
-1.000 0.2550 0.02473 0.01953 -0.0791 0.7331 0.8163
-0.750 0.2696 0.02484 0.01969 -0.0743 0.7315 0.8688
-0.500 0.2394 0.02638 0.02128 -0.0662 0.7204 0.8820
-0.250 0.2462 0.02633 0.02128 -0.0601 0.7178 0.9289
0.000 0.3506 0.02677 0.02159 -0.0724 0.7187 0.9738
0.250 0.4069 0.02669 0.02137 -0.0775 0.7177 0.9771
0.500 0.4579 0.02651 0.02109 -0.0816 0.7167 0.9811
0.750 0.5072 0.02630 0.02078 -0.0854 0.7158 0.9844
1.000 0.5576 0.02600 0.02040 -0.0893 0.7150 0.9869
1.250 0.6061 0.02563 0.01994 -0.0928 0.7143 0.9896
1.500 0.6185 0.02720 0.02157 -0.0935 0.7027 1.0000
1.750 0.5517 0.02839 0.02278 -0.0790 0.6904 1.0000
2.000 0.5770 0.02804 0.02238 -0.0783 0.6875 1.0000
2.250 0.6165 0.02749 0.02177 -0.0797 0.6861 1.0000
2.500 0.6577 0.02674 0.02099 -0.0812 0.6851 1.0000
2.750 0.7012 0.02588 0.02008 -0.0829 0.6843 1.0000
3.000 0.7447 0.02498 0.01914 -0.0847 0.6836 1.0000
3.250 0.7135 0.02635 0.02052 -0.0765 0.6704 1.0000
3.500 0.7024 0.02762 0.02177 -0.0717 0.6588 1.0000
3.750 0.7469 0.02664 0.02079 -0.0734 0.6576 1.0000
4.000 0.7951 0.02548 0.01962 -0.0757 0.6569 1.0000
4.250 0.8431 0.02422 0.01836 -0.0779 0.6562 1.0000
4.500 0.8899 0.02295 0.01708 -0.0800 0.6554 1.0000
4.750 0.9367 0.02174 0.01587 -0.0823 0.6544 1.0000
5.000 0.9776 0.02080 0.01493 -0.0838 0.6520 1.0000
5.250 0.9843 0.02118 0.01536 -0.0807 0.6421 1.0000
5.500 1.0316 0.01991 0.01411 -0.0831 0.6401 1.0000
5.750 1.0817 0.01858 0.01276 -0.0859 0.6379 1.0000
6.000 1.0858 0.01897 0.01323 -0.0823 0.6269 1.0000
6.250 1.1346 0.01772 0.01197 -0.0850 0.6231 1.0000
6.500 1.1412 0.01794 0.01227 -0.0816 0.6117 1.0000
6.750 1.1600 0.01773 0.01210 -0.0799 0.6014 1.0000
7.000 1.1885 0.01716 0.01154 -0.0796 0.5907 1.0000
7.250 1.2042 0.01701 0.01139 -0.0773 0.5764 1.0000
7.500 1.2125 0.01719 0.01158 -0.0740 0.5587 1.0000
7.750 1.2248 0.01734 0.01168 -0.0715 0.5378 1.0000
8.000 1.2388 0.01754 0.01179 -0.0694 0.5129 1.0000
8.250 1.2483 0.01805 0.01213 -0.0668 0.4835 1.0000
8.500 1.2523 0.01893 0.01282 -0.0638 0.4521 1.0000
8.750 1.2525 0.02012 0.01380 -0.0605 0.4211 1.0000
9.250 1.2500 0.02297 0.01630 -0.0544 0.3656 1.0000
9.500 1.2498 0.02446 0.01764 -0.0516 0.3421 1.0000
9.750 1.2514 0.02592 0.01899 -0.0493 0.3205 1.0000
10.000 1.2532 0.02743 0.02038 -0.0470 0.3011 1.0000
10.250 1.2562 0.02891 0.02176 -0.0450 0.2836 1.0000
10.500 1.2602 0.03038 0.02314 -0.0431 0.2674 1.0000
10.750 1.2649 0.03185 0.02455 -0.0414 0.2522 1.0000
11.000 1.2707 0.03328 0.02594 -0.0399 0.2381 1.0000
11.250 1.2773 0.03472 0.02735 -0.0385 0.2253 1.0000
11.500 1.2847 0.03614 0.02875 -0.0372 0.2140 1.0000
11.750 1.2915 0.03764 0.03017 -0.0359 0.2036 1.0000
12.000 1.2997 0.03909 0.03163 -0.0349 0.1935 1.0000
12.250 1.3085 0.04052 0.03307 -0.0338 0.1843 1.0000
12.500 1.3165 0.04203 0.03449 -0.0328 0.1760 1.0000
12.750 1.3260 0.04348 0.03605 -0.0320 0.1680 1.0000
13.000 1.3357 0.04490 0.03734 -0.0311 0.1607 1.0000
13.250 1.3453 0.04640 0.03898 -0.0304 0.1542 1.0000
13.500 1.3556 0.04783 0.04037 -0.0296 0.1486 1.0000
13.750 1.3678 0.04915 0.04175 -0.0289 0.1433 1.0000
14.000 1.3785 0.05060 0.04329 -0.0283 0.1386 1.0000
14.250 1.3913 0.05186 0.04450 -0.0278 0.1340 1.0000
14.500 1.4038 0.05323 0.04596 -0.0272 0.1301 1.0000
14.750 1.4129 0.05488 0.04774 -0.0267 0.1262 1.0000
15.000 1.4246 0.05630 0.04920 -0.0262 0.1229 1.0000
15.250 1.4456 0.05702 0.04985 -0.0259 0.1189 1.0000
15.500 1.4487 0.05922 0.05228 -0.0254 0.1162 1.0000
15.750 1.4544 0.06123 0.05442 -0.0250 0.1129 1.0000
16.000 1.4621 0.06304 0.05628 -0.0247 0.1098 1.0000
16.250 1.4823 0.06382 0.05698 -0.0245 0.1060 1.0000
16.500 1.4814 0.06653 0.05993 -0.0242 0.1041 1.0000
16.750 1.4837 0.06903 0.06263 -0.0240 0.1016 1.0000
17.000 1.4867 0.07139 0.06511 -0.0239 0.0988 1.0000
17.250 1.4919 0.07352 0.06725 -0.0240 0.0959 1.0000
17.500 1.4999 0.07551 0.06928 -0.0239 0.0928 1.0000
17.750 1.4929 0.07918 0.07320 -0.0243 0.0906 1.0000
18.000 1.4897 0.08251 0.07668 -0.0248 0.0879 1.0000
18.250 1.4908 0.08529 0.07953 -0.0253 0.0853 1.0000
18.500 1.5016 0.08682 0.08097 -0.0254 0.0819 1.0000
18.750 1.4904 0.09143 0.08587 -0.0265 0.0803 1.0000
19.000 1.4821 0.09578 0.09044 -0.0277 0.0780 1.0000
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