NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.26 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0115-il-1000000-n5.txt Download as CSV file: xf-nlf0115-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLF(1)-0115
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7768 0.06319 0.06072 -0.0751 1.0000 0.0076
-14.750 -0.7986 0.05732 0.05468 -0.0773 1.0000 0.0074
-14.500 -0.8355 0.05080 0.04794 -0.0785 1.0000 0.0075
-14.250 -0.8575 0.04668 0.04366 -0.0779 1.0000 0.0075
-14.000 -0.8720 0.04369 0.04054 -0.0766 1.0000 0.0076
-13.750 -0.8756 0.04037 0.03705 -0.0775 0.9991 0.0076
-13.500 -0.8740 0.03747 0.03401 -0.0786 0.9975 0.0077
-13.250 -0.8717 0.03467 0.03101 -0.0792 0.9952 0.0076
-13.000 -0.8628 0.03280 0.02904 -0.0796 0.9928 0.0077
-12.750 -0.8544 0.03075 0.02684 -0.0799 0.9901 0.0078
-12.500 -0.8404 0.02920 0.02518 -0.0805 0.9879 0.0078
-12.250 -0.8227 0.02789 0.02378 -0.0813 0.9861 0.0079
-12.000 -0.8035 0.02639 0.02215 -0.0823 0.9845 0.0080
-11.750 -0.7860 0.02505 0.02070 -0.0827 0.9816 0.0080
-11.500 -0.7677 0.02377 0.01930 -0.0829 0.9781 0.0081
-11.250 -0.7457 0.02253 0.01793 -0.0836 0.9750 0.0081
-11.000 -0.7202 0.02154 0.01685 -0.0848 0.9724 0.0082
-10.750 -0.7042 0.02072 0.01595 -0.0837 0.9661 0.0083
-10.500 -0.6818 0.01993 0.01508 -0.0838 0.9609 0.0084
-10.250 -0.6647 0.01903 0.01407 -0.0827 0.9535 0.0085
-10.000 -0.6446 0.01831 0.01327 -0.0821 0.9445 0.0086
-9.500 -0.6079 0.01712 0.01188 -0.0796 0.9037 0.0089
-9.250 -0.5922 0.01663 0.01117 -0.0777 0.8646 0.0090
-9.000 -0.5780 0.01623 0.01059 -0.0754 0.8349 0.0091
-8.750 -0.5616 0.01583 0.01005 -0.0736 0.8132 0.0093
-8.500 -0.5437 0.01541 0.00950 -0.0721 0.7958 0.0095
-8.250 -0.5249 0.01501 0.00900 -0.0707 0.7816 0.0096
-8.000 -0.5057 0.01459 0.00849 -0.0694 0.7701 0.0097
-7.750 -0.4861 0.01421 0.00802 -0.0682 0.7597 0.0098
-7.500 -0.4653 0.01385 0.00760 -0.0671 0.7505 0.0099
-7.250 -0.4449 0.01349 0.00716 -0.0660 0.7424 0.0099
-7.000 -0.4236 0.01314 0.00675 -0.0650 0.7347 0.0101
-6.750 -0.4052 0.01261 0.00616 -0.0636 0.7278 0.0104
-6.500 -0.3838 0.01225 0.00576 -0.0626 0.7215 0.0106
-6.250 -0.3617 0.01195 0.00542 -0.0617 0.7151 0.0109
-6.000 -0.3389 0.01168 0.00511 -0.0610 0.7095 0.0110
-5.750 -0.3156 0.01141 0.00482 -0.0603 0.7039 0.0113
-5.500 -0.2921 0.01118 0.00455 -0.0596 0.6987 0.0116
-5.250 -0.2683 0.01094 0.00428 -0.0590 0.6945 0.0119
-5.000 -0.2439 0.01071 0.00402 -0.0585 0.6903 0.0122
-4.750 -0.2193 0.01051 0.00379 -0.0580 0.6861 0.0125
-4.500 -0.1946 0.01032 0.00357 -0.0576 0.6822 0.0129
-4.250 -0.1692 0.01017 0.00339 -0.0572 0.6789 0.0132
-4.000 -0.1444 0.00992 0.00314 -0.0568 0.6755 0.0141
-3.750 -0.1189 0.00975 0.00296 -0.0564 0.6719 0.0149
-3.500 -0.0932 0.00961 0.00279 -0.0561 0.6684 0.0155
-3.000 -0.0409 0.00935 0.00251 -0.0557 0.6625 0.0178
-2.750 -0.0146 0.00920 0.00237 -0.0555 0.6598 0.0215
-2.500 0.0107 0.00897 0.00224 -0.0552 0.6571 0.0427
-2.250 0.0359 0.00874 0.00212 -0.0548 0.6545 0.0738
-2.000 0.0588 0.00832 0.00196 -0.0542 0.6519 0.1546
-1.500 0.0904 0.00628 0.00145 -0.0507 0.6469 0.6158
-1.250 0.1187 0.00631 0.00149 -0.0508 0.6445 0.6336
-1.000 0.1471 0.00636 0.00154 -0.0509 0.6423 0.6461
-0.750 0.1755 0.00644 0.00160 -0.0510 0.6400 0.6548
-0.500 0.2037 0.00648 0.00163 -0.0511 0.6370 0.6610
-0.250 0.2315 0.00650 0.00161 -0.0512 0.6309 0.6622
0.000 0.2595 0.00652 0.00159 -0.0512 0.6223 0.6630
0.250 0.2871 0.00655 0.00158 -0.0512 0.6142 0.6639
0.500 0.3146 0.00658 0.00156 -0.0512 0.6044 0.6648
0.750 0.3424 0.00661 0.00156 -0.0512 0.5956 0.6656
1.000 0.3697 0.00666 0.00156 -0.0512 0.5866 0.6663
1.250 0.3979 0.00669 0.00158 -0.0513 0.5799 0.6671
1.500 0.4253 0.00674 0.00159 -0.0513 0.5715 0.6679
1.750 0.4529 0.00678 0.00161 -0.0513 0.5612 0.6687
2.000 0.4800 0.00684 0.00164 -0.0512 0.5495 0.6694
2.250 0.5057 0.00696 0.00167 -0.0509 0.5270 0.6702
2.500 0.5280 0.00724 0.00176 -0.0499 0.4815 0.6710
2.750 0.5478 0.00768 0.00194 -0.0485 0.4238 0.6718
3.000 0.5672 0.00816 0.00217 -0.0471 0.3688 0.6725
3.250 0.5874 0.00858 0.00238 -0.0458 0.3214 0.6731
3.500 0.6095 0.00888 0.00254 -0.0449 0.2905 0.6741
3.750 0.6321 0.00914 0.00270 -0.0441 0.2655 0.6752
4.000 0.6547 0.00939 0.00287 -0.0432 0.2443 0.6764
4.250 0.6773 0.00963 0.00304 -0.0424 0.2246 0.6775
4.500 0.7000 0.00986 0.00320 -0.0416 0.2087 0.6786
4.750 0.7229 0.01007 0.00337 -0.0408 0.1963 0.6796
5.000 0.7453 0.01029 0.00354 -0.0399 0.1835 0.6806
5.250 0.7674 0.01052 0.00371 -0.0390 0.1721 0.6817
5.500 0.7902 0.01070 0.00388 -0.0382 0.1640 0.6829
5.750 0.8118 0.01092 0.00407 -0.0372 0.1557 0.6840
6.000 0.8332 0.01110 0.00424 -0.0361 0.1489 0.6851
6.250 0.8524 0.01132 0.00442 -0.0346 0.1410 0.6863
6.500 0.8726 0.01150 0.00461 -0.0333 0.1355 0.6874
6.750 0.8918 0.01175 0.00483 -0.0319 0.1295 0.6884
7.000 0.9119 0.01197 0.00505 -0.0306 0.1246 0.6894
7.250 0.9311 0.01223 0.00530 -0.0292 0.1188 0.6909
7.500 0.9499 0.01250 0.00557 -0.0277 0.1137 0.6924
7.750 0.9700 0.01272 0.00582 -0.0265 0.1108 0.6939
8.000 0.9889 0.01300 0.00610 -0.0252 0.1059 0.6954
8.250 1.0068 0.01332 0.00642 -0.0237 0.1009 0.6972
8.500 1.0263 0.01359 0.00671 -0.0224 0.0983 0.6990
8.750 1.0450 0.01389 0.00703 -0.0211 0.0945 0.7009
9.000 1.0625 0.01424 0.00738 -0.0196 0.0909 0.7029
9.250 1.0802 0.01459 0.00774 -0.0182 0.0870 0.7047
9.500 1.0981 0.01493 0.00811 -0.0169 0.0837 0.7065
9.750 1.1149 0.01532 0.00851 -0.0154 0.0803 0.7088
10.000 1.1307 0.01576 0.00896 -0.0138 0.0760 0.7112
10.250 1.1475 0.01617 0.00939 -0.0124 0.0725 0.7137
10.500 1.1641 0.01660 0.00986 -0.0110 0.0702 0.7163
10.750 1.1780 0.01717 0.01041 -0.0093 0.0651 0.7190
11.000 1.1940 0.01766 0.01093 -0.0080 0.0622 0.7216
11.250 1.2095 0.01816 0.01148 -0.0066 0.0601 0.7248
11.500 1.2230 0.01879 0.01212 -0.0051 0.0568 0.7284
11.750 1.2374 0.01939 0.01276 -0.0037 0.0537 0.7323
12.000 1.2514 0.02005 0.01344 -0.0023 0.0507 0.7362
12.250 1.2642 0.02077 0.01420 -0.0009 0.0479 0.7407
12.500 1.2772 0.02150 0.01496 0.0005 0.0452 0.7460
12.750 1.2905 0.02225 0.01575 0.0018 0.0428 0.7518
13.000 1.3021 0.02310 0.01665 0.0031 0.0402 0.7582
13.250 1.3133 0.02399 0.01759 0.0044 0.0373 0.7666
13.500 1.3255 0.02484 0.01850 0.0056 0.0355 0.7759
13.750 1.3352 0.02585 0.01957 0.0070 0.0327 0.7892
14.000 1.3451 0.02684 0.02064 0.0083 0.0305 0.8068
14.250 1.3543 0.02779 0.02173 0.0097 0.0286 0.8371
14.500 1.3814 0.02898 0.02325 0.0069 0.0257 0.9557
14.750 1.3941 0.03019 0.02450 0.0072 0.0240 1.0000
15.000 1.4020 0.03159 0.02592 0.0082 0.0217 1.0000
15.250 1.4109 0.03295 0.02732 0.0090 0.0204 1.0000
15.500 1.4176 0.03451 0.02892 0.0098 0.0178 1.0000
15.750 1.4223 0.03628 0.03071 0.0107 0.0152 1.0000
16.000 1.4235 0.03840 0.03284 0.0116 0.0116 1.0000
16.250 1.4263 0.04045 0.03493 0.0123 0.0098 1.0000
16.750 1.4293 0.04496 0.03955 0.0133 0.0070 1.0000
17.000 1.4298 0.04741 0.04206 0.0137 0.0062 1.0000
17.250 1.4325 0.04971 0.04445 0.0138 0.0059 1.0000
17.500 1.4333 0.05229 0.04710 0.0139 0.0056 1.0000
17.750 1.4328 0.05507 0.04997 0.0138 0.0052 1.0000
18.000 1.4336 0.05779 0.05277 0.0136 0.0052 1.0000
18.250 1.4293 0.06118 0.05625 0.0132 0.0049 1.0000
18.500 1.4259 0.06460 0.05976 0.0125 0.0047 1.0000
19.000 1.4143 0.07240 0.06777 0.0106 0.0044 1.0000
19.250 1.4072 0.07669 0.07217 0.0092 0.0044 1.0000
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Polar data table (+)
Polar graphs
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