NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA LRN 1015 (NASA TM 102840) (lrn1015-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.37 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lrn1015-il-1000000-n5.txt Download as CSV file: xf-lrn1015-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1234 0.08652 0.08339 -0.1057 0.7222 0.0067
-11.250 -0.1286 0.08138 0.07825 -0.1079 0.7210 0.0065
-11.000 -0.1372 0.07592 0.07283 -0.1106 0.7198 0.0067
-10.750 -0.1534 0.06906 0.06600 -0.1143 0.7184 0.0067
-10.500 -0.3021 0.04185 0.03859 -0.1297 0.7159 0.0068
-10.250 -0.2364 0.04723 0.04410 -0.1296 0.7148 0.0069
-10.000 -0.2956 0.04044 0.03709 -0.1260 0.7124 0.0069
-9.750 -0.4093 0.02335 0.01879 -0.1153 0.7105 0.0073
-9.500 -0.3943 0.02196 0.01722 -0.1140 0.7091 0.0074
-9.250 -0.3800 0.02025 0.01527 -0.1125 0.7077 0.0076
-9.000 -0.3624 0.01890 0.01371 -0.1114 0.7063 0.0077
-8.750 -0.3425 0.01779 0.01243 -0.1104 0.7049 0.0078
-8.500 -0.3213 0.01683 0.01133 -0.1096 0.7035 0.0080
-8.250 -0.2986 0.01607 0.01043 -0.1090 0.7021 0.0082
-8.000 -0.2752 0.01541 0.00965 -0.1084 0.7006 0.0084
-7.750 -0.2508 0.01490 0.00903 -0.1079 0.6991 0.0086
-7.500 -0.2263 0.01439 0.00843 -0.1075 0.6975 0.0087
-7.250 -0.2015 0.01388 0.00784 -0.1071 0.6962 0.0088
-7.000 -0.1783 0.01311 0.00699 -0.1064 0.6951 0.0091
-6.750 -0.1528 0.01272 0.00657 -0.1061 0.6938 0.0092
-6.500 -0.1270 0.01234 0.00616 -0.1059 0.6924 0.0094
-6.250 -0.1008 0.01203 0.00583 -0.1056 0.6909 0.0096
-6.000 -0.0746 0.01173 0.00550 -0.1054 0.6893 0.0098
-5.750 -0.0484 0.01142 0.00516 -0.1052 0.6877 0.0101
-5.500 -0.0221 0.01113 0.00482 -0.1049 0.6863 0.0103
-5.250 0.0042 0.01083 0.00448 -0.1047 0.6849 0.0105
-5.000 0.0306 0.01056 0.00417 -0.1045 0.6835 0.0108
-4.750 0.0573 0.01034 0.00391 -0.1043 0.6819 0.0110
-4.500 0.0844 0.01012 0.00367 -0.1042 0.6806 0.0112
-4.250 0.1111 0.00983 0.00338 -0.1040 0.6791 0.0117
-4.000 0.1385 0.00965 0.00320 -0.1040 0.6777 0.0122
-3.750 0.1661 0.00949 0.00306 -0.1040 0.6762 0.0129
-3.500 0.1937 0.00933 0.00288 -0.1039 0.6746 0.0134
-3.250 0.2213 0.00918 0.00271 -0.1039 0.6729 0.0139
-3.000 0.2487 0.00900 0.00253 -0.1039 0.6712 0.0147
-2.750 0.2765 0.00887 0.00240 -0.1039 0.6696 0.0156
-2.500 0.3043 0.00877 0.00228 -0.1039 0.6680 0.0168
-2.250 0.3320 0.00867 0.00217 -0.1039 0.6663 0.0182
-2.000 0.3601 0.00856 0.00208 -0.1040 0.6648 0.0204
-1.750 0.3882 0.00846 0.00201 -0.1041 0.6632 0.0240
-1.500 0.4162 0.00835 0.00194 -0.1041 0.6613 0.0308
-1.250 0.4435 0.00815 0.00187 -0.1041 0.6594 0.0697
-1.000 0.4691 0.00772 0.00179 -0.1040 0.6574 0.1911
-0.750 0.4929 0.00707 0.00171 -0.1037 0.6553 0.3875
-0.500 0.5149 0.00635 0.00166 -0.1031 0.6532 0.6152
-0.250 0.5398 0.00613 0.00174 -0.1025 0.6510 0.7205
0.000 0.5674 0.00611 0.00181 -0.1024 0.6489 0.7560
0.250 0.5956 0.00613 0.00186 -0.1024 0.6458 0.7727
0.500 0.6239 0.00615 0.00185 -0.1025 0.6411 0.7803
0.750 0.6514 0.00618 0.00185 -0.1024 0.6354 0.7858
1.000 0.6796 0.00620 0.00187 -0.1025 0.6295 0.7915
1.250 0.7075 0.00624 0.00188 -0.1026 0.6239 0.7967
1.500 0.7352 0.00629 0.00191 -0.1026 0.6192 0.8010
1.750 0.7631 0.00632 0.00195 -0.1027 0.6129 0.8053
2.000 0.7900 0.00639 0.00198 -0.1025 0.6057 0.8096
2.250 0.8178 0.00645 0.00203 -0.1026 0.5981 0.8133
2.500 0.8444 0.00653 0.00208 -0.1025 0.5905 0.8166
2.750 0.8713 0.00660 0.00214 -0.1024 0.5809 0.8196
3.000 0.8972 0.00670 0.00222 -0.1021 0.5699 0.8228
3.250 0.9218 0.00686 0.00232 -0.1016 0.5534 0.8261
3.500 0.9450 0.00708 0.00245 -0.1008 0.5331 0.8294
3.750 0.9667 0.00736 0.00263 -0.0998 0.5099 0.8324
4.000 0.9867 0.00768 0.00285 -0.0984 0.4847 0.8358
4.250 1.0050 0.00806 0.00312 -0.0968 0.4566 0.8394
4.500 1.0206 0.00853 0.00344 -0.0947 0.4243 0.8434
4.750 1.0359 0.00899 0.00377 -0.0926 0.3956 0.8471
5.000 1.0495 0.00946 0.00412 -0.0902 0.3684 0.8507
5.250 1.0585 0.00999 0.00452 -0.0869 0.3379 0.8550
5.500 1.0619 0.01051 0.00492 -0.0825 0.3104 0.8602
6.000 1.0764 0.01150 0.00578 -0.0755 0.2740 0.8707
6.250 1.0842 0.01202 0.00627 -0.0723 0.2599 0.8773
6.500 1.0902 0.01266 0.00688 -0.0691 0.2457 0.8844
6.750 1.0961 0.01340 0.00761 -0.0661 0.2318 0.8942
7.000 1.1051 0.01408 0.00830 -0.0637 0.2206 0.9072
7.250 1.1166 0.01474 0.00900 -0.0618 0.2104 0.9294
7.500 1.1492 0.01551 0.00976 -0.0646 0.1960 0.9643
7.750 1.1639 0.01626 0.01048 -0.0635 0.1868 1.0000
8.000 1.1773 0.01702 0.01121 -0.0621 0.1775 1.0000
8.250 1.1890 0.01788 0.01202 -0.0606 0.1672 1.0000
8.500 1.2024 0.01866 0.01277 -0.0593 0.1594 1.0000
8.750 1.2159 0.01944 0.01353 -0.0581 0.1524 1.0000
9.000 1.2300 0.02020 0.01427 -0.0569 0.1458 1.0000
9.250 1.2429 0.02104 0.01509 -0.0556 0.1394 1.0000
9.500 1.2570 0.02181 0.01585 -0.0545 0.1337 1.0000
9.750 1.2694 0.02270 0.01672 -0.0533 0.1271 1.0000
10.000 1.2836 0.02349 0.01752 -0.0523 0.1226 1.0000
10.250 1.2965 0.02436 0.01838 -0.0511 0.1172 1.0000
10.500 1.3094 0.02524 0.01925 -0.0501 0.1119 1.0000
10.750 1.3222 0.02616 0.02017 -0.0490 0.1071 1.0000
11.000 1.3339 0.02715 0.02114 -0.0479 0.1017 1.0000
11.250 1.3479 0.02800 0.02202 -0.0470 0.0984 1.0000
11.500 1.3605 0.02899 0.02302 -0.0461 0.0946 1.0000
11.750 1.3722 0.03007 0.02408 -0.0451 0.0898 1.0000
12.000 1.3860 0.03101 0.02504 -0.0443 0.0871 1.0000
12.250 1.3976 0.03213 0.02617 -0.0434 0.0829 1.0000
12.500 1.4086 0.03330 0.02733 -0.0425 0.0788 1.0000
12.750 1.4214 0.03436 0.02842 -0.0417 0.0758 1.0000
13.000 1.4328 0.03555 0.02963 -0.0410 0.0728 1.0000
13.250 1.4433 0.03684 0.03091 -0.0402 0.0695 1.0000
13.500 1.4547 0.03805 0.03214 -0.0394 0.0666 1.0000
13.750 1.4660 0.03930 0.03343 -0.0388 0.0644 1.0000
14.000 1.4775 0.04054 0.03471 -0.0381 0.0629 1.0000
14.250 1.4871 0.04195 0.03613 -0.0374 0.0602 1.0000
14.500 1.4960 0.04347 0.03766 -0.0368 0.0573 1.0000
14.750 1.5071 0.04480 0.03904 -0.0362 0.0556 1.0000
15.000 1.5174 0.04621 0.04049 -0.0357 0.0540 1.0000
15.250 1.5259 0.04781 0.04212 -0.0352 0.0522 1.0000
15.500 1.5332 0.04952 0.04384 -0.0346 0.0493 1.0000
15.750 1.5420 0.05114 0.04551 -0.0341 0.0474 1.0000
16.000 1.5497 0.05289 0.04729 -0.0337 0.0450 1.0000
16.250 1.5565 0.05473 0.04916 -0.0333 0.0430 1.0000
16.500 1.5621 0.05674 0.05121 -0.0329 0.0407 1.0000
16.750 1.5687 0.05864 0.05315 -0.0326 0.0381 1.0000
17.000 1.5704 0.06112 0.05564 -0.0322 0.0343 1.0000
17.250 1.5736 0.06347 0.05802 -0.0320 0.0307 1.0000
17.500 1.5720 0.06641 0.06096 -0.0317 0.0261 1.0000
17.750 1.5689 0.06958 0.06415 -0.0316 0.0221 1.0000
18.000 1.5651 0.07291 0.06751 -0.0316 0.0188 1.0000
18.250 1.5624 0.07621 0.07086 -0.0318 0.0168 1.0000
18.500 1.5585 0.07975 0.07446 -0.0321 0.0143 1.0000
18.750 1.5554 0.08325 0.07803 -0.0326 0.0125 1.0000
19.000 1.5495 0.08719 0.08203 -0.0332 0.0100 1.0000
19.250 1.5375 0.09209 0.08698 -0.0342 0.0068 1.0000
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