NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Reynolds number: 500,000 Max Cl/Cd: 127.7 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lrn1015-il-500000.txt Download as CSV file: xf-lrn1015-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0268 0.08901 0.08570 -0.0970 0.7685 0.0208
-11.000 -0.0240 0.08546 0.08216 -0.0983 0.7673 0.0213
-10.750 -0.0227 0.08163 0.07833 -0.0998 0.7662 0.0219
-10.500 -0.0238 0.07736 0.07406 -0.1016 0.7651 0.0224
-10.250 -0.0393 0.07000 0.06672 -0.1062 0.7641 0.0231
-10.000 -0.0470 0.06416 0.06088 -0.1094 0.7631 0.0231
-9.750 -0.0613 0.05609 0.05280 -0.1152 0.7619 0.0231
-9.500 -0.0877 0.06351 0.06006 -0.1262 0.7645 0.0230
-9.000 -0.1100 0.04154 0.03820 -0.1218 0.7569 0.0235
-8.750 -0.1310 0.03866 0.03525 -0.1205 0.7547 0.0235
-8.500 -0.1388 0.03638 0.03294 -0.1186 0.7528 0.0236
-8.250 -0.1394 0.03401 0.03052 -0.1174 0.7512 0.0237
-8.000 -0.1374 0.03172 0.02817 -0.1163 0.7496 0.0240
-7.750 -0.1334 0.02947 0.02582 -0.1152 0.7482 0.0243
-7.500 -0.1283 0.02708 0.02331 -0.1140 0.7466 0.0248
-7.250 -0.1219 0.02459 0.02068 -0.1128 0.7449 0.0256
-7.000 -0.1272 0.02129 0.01664 -0.1088 0.7427 0.0280
-6.750 -0.1127 0.01794 0.01339 -0.1090 0.7412 0.0287
-6.500 -0.0951 0.01640 0.01181 -0.1084 0.7395 0.0293
-6.250 -0.0769 0.01503 0.01035 -0.1078 0.7378 0.0305
-6.000 -0.0638 0.01297 0.00770 -0.1056 0.7360 0.0342
-5.750 -0.0417 0.01156 0.00634 -0.1057 0.7345 0.0351
-5.500 -0.0194 0.01056 0.00526 -0.1054 0.7331 0.0366
-5.250 0.0013 0.00947 0.00379 -0.1044 0.7318 0.0415
-5.000 0.0336 0.01900 0.01220 -0.1074 0.7333 0.0232
-4.750 0.0602 0.01773 0.01084 -0.1071 0.7320 0.0230
-4.500 0.0868 0.01686 0.00985 -0.1067 0.7308 0.0232
-4.250 0.1121 0.01589 0.00885 -0.1063 0.7294 0.0235
-4.000 0.1363 0.01515 0.00815 -0.1057 0.7277 0.0240
-3.750 0.1611 0.01467 0.00771 -0.1052 0.7257 0.0249
-3.500 0.1866 0.01434 0.00739 -0.1048 0.7238 0.0262
-3.250 0.2125 0.01405 0.00707 -0.1045 0.7221 0.0274
-3.000 0.2375 0.01358 0.00659 -0.1040 0.7204 0.0284
-2.750 0.2631 0.01317 0.00618 -0.1037 0.7189 0.0302
-2.500 0.2900 0.01290 0.00589 -0.1035 0.7174 0.0324
-2.250 0.3169 0.01261 0.00558 -0.1034 0.7161 0.0359
-2.000 0.3444 0.01244 0.00538 -0.1033 0.7148 0.0424
-1.750 0.3668 0.01173 0.00519 -0.1027 0.7130 0.1828
-1.500 0.3794 0.01018 0.00513 -0.1009 0.7107 0.6121
-1.250 0.4011 0.01001 0.00537 -0.0994 0.7085 0.7373
-1.000 0.4267 0.01011 0.00551 -0.0986 0.7065 0.7829
-0.750 0.4516 0.01024 0.00569 -0.0976 0.7046 0.8138
-0.500 0.4768 0.01035 0.00581 -0.0966 0.7030 0.8340
-0.250 0.5024 0.01043 0.00588 -0.0957 0.7014 0.8497
0.000 0.5299 0.01045 0.00587 -0.0954 0.7000 0.8568
0.250 0.5581 0.01053 0.00590 -0.0954 0.6982 0.8635
0.500 0.5823 0.01056 0.00597 -0.0947 0.6955 0.8689
0.750 0.6080 0.01058 0.00600 -0.0943 0.6926 0.8747
1.000 0.6357 0.01054 0.00593 -0.0942 0.6900 0.8804
1.250 0.6637 0.01037 0.00574 -0.0941 0.6873 0.8849
1.500 0.6937 0.01019 0.00550 -0.0944 0.6845 0.8895
1.750 0.7200 0.01014 0.00544 -0.0941 0.6806 0.8945
2.000 0.7456 0.01004 0.00537 -0.0936 0.6764 0.8989
2.250 0.7731 0.00990 0.00522 -0.0935 0.6729 0.9031
2.500 0.8023 0.00977 0.00505 -0.0937 0.6699 0.9074
2.750 0.8294 0.00973 0.00500 -0.0936 0.6662 0.9119
3.000 0.8536 0.00964 0.00496 -0.0929 0.6614 0.9161
3.250 0.8806 0.00952 0.00485 -0.0927 0.6573 0.9207
3.500 0.9092 0.00943 0.00472 -0.0929 0.6537 0.9252
3.750 0.9330 0.00939 0.00474 -0.0922 0.6488 0.9301
4.000 0.9578 0.00931 0.00469 -0.0916 0.6434 0.9353
4.250 0.9853 0.00921 0.00457 -0.0915 0.6386 0.9406
4.500 1.0087 0.00918 0.00462 -0.0908 0.6322 0.9465
4.750 1.0344 0.00912 0.00457 -0.0904 0.6258 0.9531
5.000 1.0610 0.00910 0.00459 -0.0903 0.6186 0.9599
5.250 1.0906 0.00909 0.00460 -0.0909 0.6103 0.9667
5.500 1.1225 0.00913 0.00468 -0.0921 0.6000 0.9740
5.750 1.1558 0.00919 0.00474 -0.0936 0.5854 0.9824
6.000 1.1889 0.00931 0.00483 -0.0952 0.5671 0.9985
6.250 1.2069 0.00952 0.00496 -0.0936 0.5467 1.0000
6.500 1.2223 0.00985 0.00519 -0.0917 0.5201 1.0000
6.750 1.2328 0.01034 0.00553 -0.0889 0.4894 1.0000
7.000 1.2359 0.01096 0.00598 -0.0847 0.4581 1.0000
7.250 1.2336 0.01170 0.00657 -0.0797 0.4290 1.0000
7.500 1.2304 0.01260 0.00734 -0.0749 0.4019 1.0000
8.000 1.2248 0.01504 0.00955 -0.0671 0.3530 1.0000
8.250 1.2243 0.01643 0.01083 -0.0640 0.3304 1.0000
8.500 1.2269 0.01773 0.01202 -0.0614 0.3089 1.0000
8.750 1.2313 0.01896 0.01317 -0.0590 0.2896 1.0000
9.000 1.2369 0.02016 0.01430 -0.0569 0.2727 1.0000
9.250 1.2434 0.02135 0.01541 -0.0549 0.2568 1.0000
9.500 1.2508 0.02249 0.01650 -0.0531 0.2423 1.0000
9.750 1.2586 0.02364 0.01760 -0.0514 0.2289 1.0000
10.000 1.2667 0.02480 0.01871 -0.0498 0.2164 1.0000
10.250 1.2741 0.02602 0.01987 -0.0482 0.2047 1.0000
10.500 1.2836 0.02714 0.02096 -0.0468 0.1930 1.0000
10.750 1.2938 0.02823 0.02204 -0.0455 0.1834 1.0000
11.000 1.3016 0.02950 0.02327 -0.0441 0.1736 1.0000
11.250 1.3115 0.03068 0.02444 -0.0429 0.1642 1.0000
11.500 1.3219 0.03187 0.02563 -0.0419 0.1565 1.0000
11.750 1.3304 0.03322 0.02695 -0.0407 0.1485 1.0000
12.000 1.3418 0.03438 0.02813 -0.0398 0.1417 1.0000
12.250 1.3497 0.03583 0.02957 -0.0387 0.1348 1.0000
12.500 1.3605 0.03709 0.03086 -0.0379 0.1290 1.0000
12.750 1.3697 0.03850 0.03227 -0.0370 0.1233 1.0000
13.000 1.3767 0.04011 0.03388 -0.0360 0.1181 1.0000
13.250 1.3882 0.04137 0.03519 -0.0353 0.1137 1.0000
13.500 1.3957 0.04301 0.03683 -0.0345 0.1094 1.0000
13.750 1.4020 0.04477 0.03861 -0.0336 0.1053 1.0000
14.000 1.4140 0.04604 0.03997 -0.0331 0.1022 1.0000
14.250 1.4221 0.04770 0.04165 -0.0325 0.0982 1.0000
14.500 1.4263 0.04974 0.04368 -0.0318 0.0944 1.0000
14.750 1.4369 0.05122 0.04524 -0.0314 0.0918 1.0000
15.000 1.4474 0.05273 0.04682 -0.0311 0.0885 1.0000
15.250 1.4543 0.05462 0.04873 -0.0307 0.0855 1.0000
15.500 1.4570 0.05693 0.05106 -0.0301 0.0828 1.0000
15.750 1.4661 0.05864 0.05286 -0.0299 0.0806 1.0000
16.000 1.4752 0.06039 0.05470 -0.0297 0.0786 1.0000
16.250 1.4823 0.06237 0.05674 -0.0296 0.0764 1.0000
16.500 1.4871 0.06463 0.05905 -0.0294 0.0742 1.0000
16.750 1.4888 0.06725 0.06170 -0.0293 0.0721 1.0000
17.000 1.4936 0.06956 0.06409 -0.0293 0.0704 1.0000
17.250 1.5014 0.07157 0.06622 -0.0294 0.0688 1.0000
17.500 1.5078 0.07380 0.06853 -0.0296 0.0665 1.0000
17.750 1.5111 0.07642 0.07120 -0.0298 0.0643 1.0000
18.000 1.5106 0.07956 0.07439 -0.0302 0.0622 1.0000
18.250 1.5121 0.08246 0.07737 -0.0306 0.0605 1.0000
18.500 1.5182 0.08483 0.07987 -0.0311 0.0587 1.0000
18.750 1.5218 0.08756 0.08270 -0.0317 0.0566 1.0000
19.000 1.5221 0.09078 0.08597 -0.0324 0.0545 1.0000
19.250 1.5182 0.09463 0.08987 -0.0334 0.0525 1.0000
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