lrn1007 (lrn1007-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: lrn1007 (lrn1007-il) Reynolds number: 100,000 Max Cl/Cd: 55.31 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lrn1007-il-100000-n5.txt Download as CSV file: xf-lrn1007-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: lrn1007
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1155 0.10680 0.10153 -0.0853 0.8964 0.0121
-8.500 -0.1064 0.10444 0.09918 -0.0870 0.8944 0.0121
-8.250 -0.0976 0.10234 0.09710 -0.0890 0.8922 0.0122
-8.000 -0.0864 0.09984 0.09460 -0.0914 0.8904 0.0122
-7.750 -0.0742 0.09722 0.09196 -0.0938 0.8890 0.0122
-7.500 -0.0616 0.09492 0.08967 -0.0967 0.8872 0.0122
-7.250 -0.0491 0.09222 0.08697 -0.0989 0.8852 0.0122
-7.000 -0.0375 0.08905 0.08385 -0.1010 0.8828 0.0123
-6.750 -0.0333 0.08338 0.07821 -0.0991 0.8812 0.0128
-6.500 -0.0232 0.07996 0.07479 -0.0996 0.8793 0.0131
-6.250 -0.0151 0.07630 0.07115 -0.0992 0.8777 0.0140
-6.000 -0.0018 0.07364 0.06838 -0.1013 0.8759 0.0145
-5.750 0.0101 0.07137 0.06612 -0.1033 0.8732 0.0150
-5.500 0.0232 0.06910 0.06385 -0.1055 0.8704 0.0155
-5.250 0.0387 0.06672 0.06145 -0.1080 0.8678 0.0161
-5.000 0.0569 0.06427 0.05898 -0.1109 0.8656 0.0166
-4.750 0.0772 0.06180 0.05644 -0.1139 0.8638 0.0174
-4.500 0.0990 0.05935 0.05392 -0.1170 0.8619 0.0183
-4.250 0.1149 0.05744 0.05198 -0.1186 0.8582 0.0196
-4.000 0.1366 0.05536 0.04981 -0.1209 0.8553 0.0210
-3.750 0.1653 0.05351 0.04782 -0.1240 0.8531 0.0227
-3.500 0.2040 0.05285 0.04685 -0.1278 0.8512 0.0240
-3.250 0.2387 0.05193 0.04561 -0.1303 0.8495 0.0244
-3.000 0.2471 0.04815 0.04192 -0.1300 0.8456 0.0253
-2.750 0.2581 0.04493 0.03877 -0.1300 0.8423 0.0279
-2.500 0.2842 0.04296 0.03665 -0.1313 0.8397 0.0319
-2.000 0.3470 0.03898 0.03223 -0.1348 0.8362 0.0426
-1.750 0.3712 0.04114 0.03382 -0.1330 0.8304 0.0505
-1.250 0.4240 0.03585 0.02824 -0.1350 0.8250 0.0650
-0.750 0.4718 0.03235 0.02450 -0.1357 0.8186 0.0977
-0.250 0.5256 0.02990 0.02161 -0.1364 0.8123 0.1601
0.250 0.5844 0.02889 0.02017 -0.1344 0.8055 0.0974
0.750 0.6430 0.02812 0.01900 -0.1321 0.7985 0.0299
1.250 0.6919 0.02721 0.01793 -0.1302 0.7891 0.0188
1.500 0.7213 0.02647 0.01715 -0.1298 0.7857 0.0160
1.750 0.7533 0.02580 0.01634 -0.1299 0.7835 0.0143
2.000 0.7714 0.02594 0.01632 -0.1285 0.7756 0.0138
2.250 0.8031 0.02557 0.01569 -0.1288 0.7722 0.0227
2.500 0.8377 0.02512 0.01503 -0.1294 0.7699 0.0457
2.750 0.8564 0.02401 0.01540 -0.1285 0.7614 1.0000
3.000 0.8873 0.02383 0.01507 -0.1286 0.7578 1.0000
3.250 0.9052 0.02418 0.01539 -0.1272 0.7490 1.0000
3.750 0.9525 0.02427 0.01549 -0.1258 0.7351 1.0000
4.000 0.9833 0.02389 0.01516 -0.1259 0.7308 1.0000
4.250 0.9994 0.02417 0.01549 -0.1242 0.7196 1.0000
4.500 1.0171 0.02435 0.01573 -0.1228 0.7088 1.0000
4.750 1.0453 0.02392 0.01536 -0.1224 0.7023 1.0000
5.000 1.0635 0.02399 0.01552 -0.1210 0.6905 1.0000
5.250 1.0804 0.02409 0.01574 -0.1193 0.6776 1.0000
5.500 1.0985 0.02404 0.01581 -0.1176 0.6649 1.0000
5.750 1.1201 0.02381 0.01576 -0.1162 0.6520 1.0000
6.000 1.1488 0.02077 0.01029 -0.1093 0.3345 1.0000
6.250 1.1389 0.02331 0.01163 -0.1043 0.1771 1.0000
6.500 1.1287 0.02663 0.01360 -0.0997 0.0057 1.0000
6.750 1.1445 0.02762 0.01481 -0.0980 0.0047 1.0000
7.000 1.1589 0.02877 0.01626 -0.0960 0.0043 1.0000
7.250 1.1718 0.03009 0.01789 -0.0940 0.0042 1.0000
7.500 1.1832 0.03158 0.01968 -0.0918 0.0042 1.0000
7.750 1.1925 0.03327 0.02166 -0.0894 0.0042 1.0000
8.000 1.1989 0.03523 0.02391 -0.0869 0.0043 1.0000
8.250 1.2030 0.03743 0.02635 -0.0842 0.0045 1.0000
8.500 1.2070 0.03975 0.02888 -0.0815 0.0046 1.0000
8.750 1.2142 0.04223 0.03154 -0.0790 0.0049 1.0000
9.750 1.3281 0.07047 0.06320 -0.0695 0.0228 1.0000
10.000 1.3121 0.07367 0.06674 -0.0654 0.0232 1.0000
10.250 1.2951 0.07698 0.07039 -0.0621 0.0239 1.0000
10.500 1.2781 0.08086 0.07454 -0.0596 0.0241 1.0000
10.750 1.2605 0.08495 0.07889 -0.0578 0.0244 1.0000
11.000 1.2422 0.08935 0.08352 -0.0567 0.0245 1.0000
11.250 1.2238 0.09399 0.08837 -0.0563 0.0245 1.0000
11.500 1.2052 0.09893 0.09349 -0.0566 0.0244 1.0000
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Polar data table (+)
Polar graphs
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