NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Reynolds number: 200,000 Max Cl/Cd: 72.58 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lrn1015-il-200000-n5.txt Download as CSV file: xf-lrn1015-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0739 0.09361 0.08869 -0.1050 0.7765 0.0291
-10.500 -0.0749 0.08971 0.08484 -0.1072 0.7747 0.0296
-10.250 -0.0852 0.08413 0.07933 -0.1114 0.7727 0.0300
-9.750 -0.0833 0.07532 0.07056 -0.1130 0.7693 0.0205
-9.500 -0.0912 0.06976 0.06503 -0.1165 0.7674 0.0206
-9.250 -0.0954 0.06539 0.06069 -0.1193 0.7654 0.0204
-9.000 -0.1013 0.06149 0.05677 -0.1218 0.7635 0.0199
-8.750 -0.1181 0.05709 0.05230 -0.1234 0.7615 0.0197
-8.500 -0.1361 0.05407 0.04922 -0.1222 0.7590 0.0196
-8.250 -0.1468 0.05068 0.04572 -0.1212 0.7566 0.0196
-8.000 -0.1524 0.04738 0.04225 -0.1199 0.7543 0.0196
-7.750 -0.1537 0.04413 0.03878 -0.1184 0.7522 0.0196
-7.500 -0.1511 0.04095 0.03534 -0.1168 0.7503 0.0192
-7.250 -0.1456 0.03766 0.03171 -0.1151 0.7484 0.0187
-7.000 -0.1374 0.03430 0.02792 -0.1132 0.7468 0.0183
-6.750 -0.1241 0.03157 0.02477 -0.1117 0.7453 0.0182
-6.500 -0.1076 0.02944 0.02230 -0.1103 0.7437 0.0182
-6.250 -0.0893 0.02776 0.02036 -0.1091 0.7416 0.0184
-6.000 -0.0689 0.02632 0.01868 -0.1082 0.7396 0.0186
-5.750 -0.0470 0.02500 0.01710 -0.1073 0.7375 0.0190
-5.500 -0.0237 0.02392 0.01577 -0.1065 0.7356 0.0199
-5.250 0.0008 0.02295 0.01448 -0.1058 0.7338 0.0208
-5.000 0.0255 0.02199 0.01346 -0.1054 0.7323 0.0214
-4.750 0.0507 0.02119 0.01258 -0.1050 0.7310 0.0218
-4.500 0.0762 0.02047 0.01180 -0.1045 0.7298 0.0224
-4.250 0.1018 0.01982 0.01109 -0.1041 0.7287 0.0231
-4.000 0.1244 0.01935 0.01060 -0.1033 0.7263 0.0239
-3.750 0.1470 0.01894 0.01017 -0.1024 0.7236 0.0247
-3.500 0.1700 0.01853 0.00980 -0.1018 0.7214 0.0262
-3.250 0.1940 0.01822 0.00950 -0.1012 0.7195 0.0282
-3.000 0.2186 0.01789 0.00912 -0.1007 0.7177 0.0299
-2.750 0.2435 0.01751 0.00872 -0.1003 0.7161 0.0318
-2.500 0.2697 0.01723 0.00838 -0.1000 0.7147 0.0349
-2.250 0.2961 0.01695 0.00808 -0.0998 0.7135 0.0407
-2.000 0.3222 0.01670 0.00783 -0.0995 0.7122 0.0518
-1.750 0.3390 0.01612 0.00790 -0.0983 0.7086 0.1961
-1.500 0.3509 0.01484 0.00798 -0.0963 0.7056 0.5507
-1.250 0.3647 0.01469 0.00854 -0.0926 0.7034 0.7500
-1.000 0.3848 0.01491 0.00881 -0.0902 0.7015 0.8061
-0.750 0.4048 0.01506 0.00896 -0.0878 0.6999 0.8390
-0.500 0.4300 0.01508 0.00891 -0.0869 0.6985 0.8521
-0.250 0.4571 0.01508 0.00881 -0.0866 0.6973 0.8604
0.000 0.4756 0.01536 0.00912 -0.0850 0.6934 0.8686
0.250 0.4967 0.01553 0.00928 -0.0838 0.6900 0.8765
0.500 0.5210 0.01559 0.00929 -0.0832 0.6875 0.8835
0.750 0.5470 0.01556 0.00922 -0.0827 0.6855 0.8898
1.000 0.5748 0.01551 0.00912 -0.0827 0.6838 0.8964
1.250 0.6033 0.01541 0.00897 -0.0827 0.6824 0.9013
1.500 0.6231 0.01562 0.00921 -0.0814 0.6785 0.9082
1.750 0.6432 0.01580 0.00941 -0.0802 0.6741 0.9149
2.000 0.6702 0.01572 0.00932 -0.0800 0.6712 0.9206
2.250 0.7004 0.01552 0.00909 -0.0804 0.6688 0.9264
2.500 0.7345 0.01522 0.00873 -0.0813 0.6666 0.9308
2.750 0.7521 0.01546 0.00906 -0.0799 0.6594 0.9392
3.000 0.7829 0.01524 0.00882 -0.0804 0.6551 0.9452
3.250 0.8192 0.01490 0.00844 -0.0818 0.6520 0.9498
3.500 0.8437 0.01508 0.00870 -0.0817 0.6453 0.9587
3.750 0.8776 0.01496 0.00859 -0.0831 0.6399 0.9651
4.000 0.9156 0.01461 0.00820 -0.0849 0.6359 0.9705
4.250 0.9433 0.01487 0.00856 -0.0857 0.6269 0.9851
4.500 0.9788 0.01462 0.00829 -0.0873 0.6214 1.0000
4.750 0.9911 0.01489 0.00861 -0.0850 0.6125 1.0000
5.000 1.0195 0.01468 0.00838 -0.0850 0.6058 1.0000
5.250 1.0341 0.01494 0.00869 -0.0831 0.5952 1.0000
5.500 1.0542 0.01502 0.00877 -0.0819 0.5848 1.0000
5.750 1.0753 0.01504 0.00877 -0.0809 0.5726 1.0000
6.000 1.0932 0.01513 0.00884 -0.0793 0.5585 1.0000
6.250 1.1097 0.01529 0.00896 -0.0774 0.5424 1.0000
6.500 1.1250 0.01550 0.00910 -0.0754 0.5222 1.0000
6.750 1.1392 0.01580 0.00926 -0.0733 0.4987 1.0000
7.000 1.1475 0.01636 0.00969 -0.0704 0.4715 1.0000
7.250 1.1509 0.01723 0.01038 -0.0672 0.4425 1.0000
7.500 1.1523 0.01833 0.01131 -0.0641 0.4147 1.0000
7.750 1.1522 0.01962 0.01242 -0.0610 0.3872 1.0000
8.000 1.1533 0.02095 0.01361 -0.0582 0.3611 1.0000
8.250 1.1555 0.02229 0.01482 -0.0557 0.3385 1.0000
8.500 1.1597 0.02357 0.01600 -0.0535 0.3177 1.0000
8.750 1.1647 0.02486 0.01719 -0.0514 0.2987 1.0000
9.000 1.1709 0.02611 0.01838 -0.0496 0.2822 1.0000
9.250 1.1781 0.02734 0.01955 -0.0479 0.2670 1.0000
9.500 1.1855 0.02858 0.02075 -0.0464 0.2527 1.0000
9.750 1.1935 0.02982 0.02194 -0.0449 0.2393 1.0000
10.000 1.2013 0.03110 0.02319 -0.0435 0.2269 1.0000
10.250 1.2090 0.03241 0.02446 -0.0421 0.2150 1.0000
10.500 1.2189 0.03361 0.02566 -0.0410 0.2042 1.0000
10.750 1.2284 0.03487 0.02692 -0.0399 0.1949 1.0000
11.000 1.2371 0.03624 0.02827 -0.0388 0.1858 1.0000
11.250 1.2476 0.03750 0.02957 -0.0379 0.1770 1.0000
11.500 1.2558 0.03897 0.03101 -0.0369 0.1690 1.0000
11.750 1.2662 0.04029 0.03237 -0.0361 0.1608 1.0000
12.000 1.2744 0.04182 0.03390 -0.0352 0.1540 1.0000
12.250 1.2851 0.04317 0.03530 -0.0345 0.1472 1.0000
12.500 1.2925 0.04484 0.03697 -0.0337 0.1415 1.0000
12.750 1.3035 0.04621 0.03841 -0.0331 0.1359 1.0000
13.000 1.3121 0.04782 0.04006 -0.0325 0.1309 1.0000
13.250 1.3195 0.04957 0.04183 -0.0318 0.1264 1.0000
13.500 1.3298 0.05108 0.04344 -0.0313 0.1216 1.0000
13.750 1.3374 0.05287 0.04528 -0.0308 0.1173 1.0000
14.000 1.3434 0.05483 0.04725 -0.0303 0.1134 1.0000
14.250 1.3533 0.05645 0.04898 -0.0299 0.1099 1.0000
14.500 1.3613 0.05828 0.05089 -0.0295 0.1066 1.0000
14.750 1.3674 0.06033 0.05299 -0.0292 0.1035 1.0000
15.000 1.3723 0.06252 0.05520 -0.0289 0.1011 1.0000
15.250 1.3817 0.06428 0.05710 -0.0286 0.0987 1.0000
15.500 1.3894 0.06623 0.05916 -0.0285 0.0961 1.0000
15.750 1.3955 0.06839 0.06142 -0.0284 0.0935 1.0000
16.000 1.4002 0.07073 0.06381 -0.0283 0.0912 1.0000
16.250 1.4039 0.07321 0.06632 -0.0283 0.0889 1.0000
16.500 1.4108 0.07540 0.06867 -0.0284 0.0866 1.0000
16.750 1.4158 0.07783 0.07124 -0.0286 0.0839 1.0000
17.000 1.4190 0.08053 0.07403 -0.0290 0.0814 1.0000
17.250 1.4206 0.08344 0.07699 -0.0294 0.0792 1.0000
17.500 1.4224 0.08639 0.08001 -0.0299 0.0769 1.0000
17.750 1.4262 0.08912 0.08292 -0.0304 0.0748 1.0000
18.000 1.4277 0.09224 0.08618 -0.0311 0.0723 1.0000
18.250 1.4273 0.09562 0.08966 -0.0320 0.0700 1.0000
18.500 1.4258 0.09917 0.09327 -0.0330 0.0681 1.0000
18.750 1.4254 0.10263 0.09685 -0.0341 0.0661 1.0000
19.000 1.4254 0.10613 0.10053 -0.0353 0.0640 1.0000
19.250 1.4242 0.10983 0.10437 -0.0366 0.0620 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA LRN 1015 (NASA TM 102840) (lrn1015-il)