NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 200,000 Max Cl/Cd: 60.82 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf0115-il-200000.txt Download as CSV file: xf-nlf0115-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4525 0.09231 0.08875 -0.0597 1.0000 0.0581
-10.500 -0.4872 0.08703 0.08343 -0.0622 1.0000 0.0583
-10.250 -0.5088 0.08350 0.07990 -0.0618 1.0000 0.0582
-10.000 -0.5398 0.08078 0.07715 -0.0599 1.0000 0.0583
-9.750 -0.5710 0.07896 0.07532 -0.0561 1.0000 0.0583
-9.500 -0.6031 0.07794 0.07432 -0.0503 1.0000 0.0583
-9.250 -0.6316 0.07624 0.07247 -0.0476 0.9961 0.0585
-9.000 -0.6368 0.06933 0.06520 -0.0517 0.9868 0.0594
-8.750 -0.6053 0.06351 0.05963 -0.0547 0.9856 0.0610
-8.500 -0.5837 0.06008 0.05617 -0.0572 0.9796 0.0626
-8.250 -0.5635 0.05656 0.05248 -0.0601 0.9735 0.0658
-8.000 -0.5637 0.05292 0.04813 -0.0609 0.9609 0.0724
-7.750 -0.5354 0.04916 0.04453 -0.0632 0.9563 0.0749
-7.500 -0.5126 0.04662 0.04185 -0.0644 0.9487 0.0788
-7.250 -0.5001 0.04377 0.03852 -0.0643 0.9390 0.0868
-7.000 -0.4704 0.04078 0.03555 -0.0662 0.9342 0.0903
-6.500 -0.4137 0.02810 0.02070 -0.0624 0.9218 0.0401
-6.250 -0.3763 0.02696 0.01928 -0.0639 0.9180 0.0392
-6.000 -0.3362 0.02446 0.01663 -0.0662 0.9159 0.0388
-5.750 -0.3088 0.02288 0.01492 -0.0660 0.9071 0.0396
-5.500 -0.2712 0.02116 0.01325 -0.0680 0.9035 0.0415
-5.250 -0.2381 0.02001 0.01208 -0.0689 0.8981 0.0424
-5.000 -0.2092 0.01904 0.01109 -0.0690 0.8910 0.0435
-4.750 -0.1772 0.01806 0.01008 -0.0698 0.8866 0.0453
-4.500 -0.1565 0.01744 0.00942 -0.0685 0.8772 0.0472
-4.250 -0.1328 0.01646 0.00844 -0.0680 0.8715 0.0503
-4.000 -0.1148 0.01600 0.00797 -0.0664 0.8626 0.0563
-3.750 -0.0928 0.01528 0.00722 -0.0655 0.8569 0.0684
-3.500 -0.0935 0.01361 0.00641 -0.0612 0.8480 0.2376
-3.250 -0.0979 0.01274 0.00712 -0.0548 0.8413 0.6591
-3.000 -0.0738 0.01361 0.00799 -0.0527 0.8356 0.6937
-2.750 -0.0495 0.01455 0.00895 -0.0504 0.8300 0.7226
-2.500 -0.0204 0.01586 0.01033 -0.0477 0.8264 0.7501
-2.250 0.0110 0.01715 0.01165 -0.0450 0.8235 0.7737
-2.000 0.0334 0.01774 0.01223 -0.0426 0.8182 0.7881
-1.750 0.0611 0.01787 0.01229 -0.0421 0.8138 0.7936
-1.500 0.0867 0.01761 0.01191 -0.0423 0.8099 0.7963
-1.250 0.1075 0.01736 0.01156 -0.0420 0.8053 0.7994
-1.000 0.1287 0.01719 0.01133 -0.0415 0.8005 0.8014
-0.750 0.1554 0.01707 0.01116 -0.0416 0.7967 0.8027
-0.500 0.1842 0.01693 0.01094 -0.0421 0.7935 0.8038
-0.250 0.2089 0.01690 0.01088 -0.0419 0.7898 0.8054
0.000 0.2307 0.01688 0.01085 -0.0414 0.7852 0.8071
0.250 0.2568 0.01679 0.01072 -0.0416 0.7813 0.8084
0.500 0.2854 0.01671 0.01059 -0.0421 0.7782 0.8101
0.750 0.3122 0.01669 0.01052 -0.0425 0.7748 0.8117
1.000 0.3328 0.01672 0.01057 -0.0418 0.7695 0.8132
1.250 0.3614 0.01658 0.01038 -0.0423 0.7642 0.8144
1.500 0.3892 0.01634 0.01007 -0.0424 0.7551 0.8161
1.750 0.4223 0.01591 0.00953 -0.0430 0.7448 0.8172
2.000 0.4444 0.01576 0.00940 -0.0419 0.7348 0.8183
2.250 0.4760 0.01559 0.00917 -0.0426 0.7290 0.8194
2.500 0.4983 0.01556 0.00919 -0.0418 0.7215 0.8207
2.750 0.5274 0.01542 0.00903 -0.0421 0.7149 0.8220
3.000 0.5527 0.01536 0.00898 -0.0417 0.7074 0.8238
3.250 0.5800 0.01523 0.00886 -0.0417 0.6998 0.8258
3.500 0.6064 0.01513 0.00877 -0.0415 0.6918 0.8275
3.750 0.6340 0.01499 0.00862 -0.0415 0.6833 0.8292
4.000 0.6591 0.01489 0.00856 -0.0412 0.6741 0.8310
4.250 0.6890 0.01469 0.00832 -0.0415 0.6649 0.8326
4.500 0.7102 0.01455 0.00826 -0.0402 0.6533 0.8343
4.750 0.7339 0.01440 0.00817 -0.0393 0.6414 0.8362
5.000 0.7576 0.01423 0.00802 -0.0384 0.6278 0.8383
5.250 0.7793 0.01406 0.00789 -0.0371 0.6115 0.8411
5.500 0.7998 0.01392 0.00778 -0.0356 0.5918 0.8441
5.750 0.8189 0.01380 0.00768 -0.0339 0.5660 0.8470
6.000 0.8332 0.01370 0.00753 -0.0312 0.5218 0.8497
6.250 0.8372 0.01398 0.00740 -0.0265 0.4437 0.8530
6.500 0.8343 0.01473 0.00772 -0.0211 0.3761 0.8572
6.750 0.8337 0.01546 0.00815 -0.0163 0.3305 0.8619
7.000 0.8375 0.01615 0.00868 -0.0124 0.2982 0.8664
7.250 0.8450 0.01683 0.00923 -0.0093 0.2739 0.8717
7.500 0.8556 0.01749 0.00980 -0.0069 0.2543 0.8780
7.750 0.8664 0.01808 0.01035 -0.0044 0.2385 0.8847
8.000 0.8796 0.01869 0.01094 -0.0025 0.2254 0.8932
8.250 0.8936 0.01933 0.01154 -0.0008 0.2142 0.9026
8.500 0.9105 0.01991 0.01214 0.0004 0.2033 0.9155
8.750 0.9336 0.02053 0.01284 0.0003 0.1927 0.9353
9.000 0.9667 0.02132 0.01365 -0.0022 0.1823 0.9898
9.250 0.9858 0.02202 0.01433 -0.0019 0.1743 1.0000
9.500 1.0058 0.02280 0.01508 -0.0017 0.1670 1.0000
9.750 1.0244 0.02351 0.01579 -0.0012 0.1603 1.0000
10.000 1.0444 0.02436 0.01659 -0.0008 0.1541 1.0000
10.250 1.0613 0.02506 0.01736 0.0000 0.1481 1.0000
10.500 1.0805 0.02593 0.01812 0.0005 0.1424 1.0000
10.750 1.0974 0.02673 0.01903 0.0014 0.1373 1.0000
11.000 1.1128 0.02752 0.01987 0.0024 0.1321 1.0000
11.250 1.1341 0.02850 0.02075 0.0026 0.1269 1.0000
11.500 1.1466 0.02935 0.02178 0.0039 0.1227 1.0000
11.750 1.1610 0.03022 0.02270 0.0050 0.1184 1.0000
12.000 1.1831 0.03130 0.02367 0.0051 0.1134 1.0000
12.250 1.1924 0.03229 0.02488 0.0066 0.1101 1.0000
12.500 1.2052 0.03331 0.02599 0.0077 0.1063 1.0000
12.750 1.2194 0.03432 0.02698 0.0085 0.1027 1.0000
13.000 1.2363 0.03561 0.02834 0.0091 0.0990 1.0000
13.250 1.2438 0.03687 0.02979 0.0105 0.0958 1.0000
13.500 1.2542 0.03807 0.03107 0.0115 0.0927 1.0000
13.750 1.2682 0.03924 0.03224 0.0122 0.0898 1.0000
14.000 1.2792 0.04082 0.03392 0.0130 0.0866 1.0000
14.250 1.2825 0.04246 0.03577 0.0143 0.0841 1.0000
14.500 1.2861 0.04395 0.03738 0.0153 0.0812 1.0000
14.750 1.2923 0.04528 0.03870 0.0161 0.0784 1.0000
15.000 1.3001 0.04709 0.04054 0.0167 0.0754 1.0000
15.250 1.2969 0.04926 0.04295 0.0177 0.0732 1.0000
15.500 1.2950 0.05131 0.04515 0.0183 0.0706 1.0000
15.750 1.2969 0.05315 0.04704 0.0186 0.0680 1.0000
16.000 1.3050 0.05496 0.04875 0.0188 0.0651 1.0000
16.250 1.2981 0.05790 0.05196 0.0190 0.0636 1.0000
16.500 1.2944 0.06088 0.05517 0.0190 0.0618 1.0000
16.750 1.2914 0.06373 0.05815 0.0187 0.0597 1.0000
17.000 1.2910 0.06639 0.06087 0.0182 0.0577 1.0000
17.250 1.2942 0.06882 0.06326 0.0180 0.0556 1.0000
17.500 1.2853 0.07290 0.06757 0.0171 0.0541 1.0000
17.750 1.2742 0.07741 0.07232 0.0157 0.0526 1.0000
18.000 1.2647 0.08193 0.07702 0.0141 0.0509 1.0000
18.250 1.2586 0.08608 0.08127 0.0123 0.0492 1.0000
18.500 1.2559 0.08977 0.08497 0.0107 0.0474 1.0000
18.750 1.2464 0.09466 0.08997 0.0087 0.0457 1.0000
19.000 1.2265 0.10171 0.09730 0.0051 0.0446 1.0000
19.250 1.2067 0.10908 0.10487 0.0011 0.0435 1.0000
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Polar data table (+)
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