NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7301 AIRFOIL (nlr7301-il) Reynolds number: 200,000 Max Cl/Cd: 30.96 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlr7301-il-200000.txt Download as CSV file: xf-nlr7301-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7301 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7040 0.10229 0.09755 -0.0504 1.0000 0.0641
-14.500 -0.7581 0.08820 0.08329 -0.0588 1.0000 0.0632
-14.250 -0.8424 0.07303 0.06771 -0.0677 1.0000 0.0618
-14.000 -0.8929 0.06453 0.05887 -0.0713 1.0000 0.0614
-13.750 -0.9234 0.05896 0.05302 -0.0728 1.0000 0.0613
-13.500 -0.9432 0.05477 0.04859 -0.0732 1.0000 0.0615
-13.250 -0.9575 0.05131 0.04490 -0.0731 1.0000 0.0618
-13.000 -0.9685 0.04832 0.04169 -0.0724 1.0000 0.0622
-12.750 -0.9779 0.04576 0.03891 -0.0710 1.0000 0.0625
-12.500 -0.9898 0.04381 0.03678 -0.0683 1.0000 0.0629
-12.250 -1.0132 0.04289 0.03576 -0.0624 1.0000 0.0630
-12.000 -1.0357 0.04204 0.03479 -0.0565 1.0000 0.0632
-11.750 -1.0505 0.04090 0.03349 -0.0516 1.0000 0.0635
-11.500 -1.0600 0.03966 0.03204 -0.0475 1.0000 0.0639
-11.250 -1.0658 0.03840 0.03054 -0.0438 1.0000 0.0644
-11.000 -1.0509 0.03712 0.02931 -0.0423 1.0000 0.0651
-10.750 -1.0258 0.03607 0.02829 -0.0429 0.9982 0.0662
-10.500 -0.9972 0.03500 0.02717 -0.0442 0.9955 0.0676
-10.250 -0.9692 0.03370 0.02569 -0.0457 0.9930 0.0693
-10.000 -0.9449 0.03240 0.02413 -0.0464 0.9898 0.0707
-9.750 -0.9159 0.03137 0.02322 -0.0470 0.9876 0.0721
-9.500 -0.8873 0.03052 0.02236 -0.0479 0.9849 0.0737
-9.250 -0.8572 0.02964 0.02139 -0.0491 0.9824 0.0757
-9.000 -0.8251 0.02869 0.02033 -0.0506 0.9804 0.0779
-8.750 -0.7973 0.02799 0.01976 -0.0510 0.9776 0.0800
-8.500 -0.7727 0.02735 0.01908 -0.0511 0.9736 0.0824
-8.250 -0.7448 0.02665 0.01827 -0.0516 0.9707 0.0850
-8.000 -0.7148 0.02594 0.01772 -0.0524 0.9686 0.0876
-7.750 -0.6828 0.02537 0.01713 -0.0538 0.9667 0.0913
-7.500 -0.6531 0.02472 0.01655 -0.0547 0.9648 0.0948
-7.250 -0.6383 0.02429 0.01616 -0.0529 0.9595 0.0980
-7.000 -0.6115 0.02373 0.01559 -0.0532 0.9560 0.1023
-6.750 -0.5821 0.02316 0.01513 -0.0542 0.9534 0.1074
-6.500 -0.5511 0.02257 0.01459 -0.0555 0.9515 0.1136
-6.250 -0.5174 0.02212 0.01416 -0.0573 0.9499 0.1212
-6.000 -0.5095 0.02166 0.01382 -0.0545 0.9442 0.1266
-5.750 -0.4858 0.02115 0.01338 -0.0545 0.9403 0.1356
-5.500 -0.4561 0.02058 0.01290 -0.0557 0.9373 0.1478
-5.250 -0.4244 0.01990 0.01239 -0.0575 0.9353 0.1650
-5.000 -0.3901 0.01913 0.01186 -0.0600 0.9336 0.1948
-4.750 -0.3532 0.01779 0.01110 -0.0639 0.9324 0.2825
-4.500 -0.3329 0.01649 0.01086 -0.0646 0.9280 0.4606
-4.250 -0.3097 0.01674 0.01136 -0.0636 0.9237 0.5362
-4.000 -0.2817 0.01715 0.01180 -0.0634 0.9206 0.5669
-3.750 -0.2505 0.01761 0.01228 -0.0635 0.9179 0.5877
-3.500 -0.2152 0.01807 0.01270 -0.0645 0.9157 0.6047
-3.250 -0.1815 0.01875 0.01344 -0.0646 0.9139 0.6161
-3.000 -0.1613 0.01922 0.01388 -0.0631 0.9096 0.6264
-2.750 -0.1488 0.01985 0.01457 -0.0595 0.9033 0.6326
-2.500 -0.1189 0.02023 0.01491 -0.0597 0.8997 0.6429
-2.250 -0.0880 0.02070 0.01543 -0.0594 0.8968 0.6491
-2.000 -0.0550 0.02132 0.01609 -0.0592 0.8945 0.6547
-1.750 -0.0144 0.02171 0.01648 -0.0610 0.8929 0.6641
-1.500 -0.0154 0.02228 0.01709 -0.0555 0.8831 0.6705
-1.250 0.0031 0.02334 0.01826 -0.0514 0.8777 0.6778
-1.000 0.0554 0.02354 0.01846 -0.0542 0.8740 0.6912
-0.750 0.0909 0.02336 0.01831 -0.0531 0.8644 0.6943
-0.500 0.1401 0.02234 0.01730 -0.0539 0.8532 0.6969
-0.250 0.1786 0.02146 0.01639 -0.0535 0.8418 0.7001
0.000 0.2126 0.02069 0.01560 -0.0535 0.8313 0.7043
0.250 0.2539 0.01983 0.01467 -0.0557 0.8256 0.7096
0.500 0.2792 0.01935 0.01420 -0.0556 0.8130 0.7137
0.750 0.3108 0.01873 0.01358 -0.0548 0.8044 0.7157
1.000 0.3335 0.01841 0.01330 -0.0530 0.7900 0.7177
1.250 0.3610 0.01790 0.01279 -0.0518 0.7738 0.7201
1.500 0.3873 0.01740 0.01228 -0.0506 0.7494 0.7231
1.750 0.4145 0.01688 0.01167 -0.0498 0.7107 0.7263
2.000 0.4391 0.01659 0.01079 -0.0485 0.5806 0.7296
2.250 0.4428 0.01809 0.01088 -0.0454 0.3415 0.7346
2.500 0.4496 0.01919 0.01128 -0.0421 0.2190 0.7367
2.750 0.4664 0.01981 0.01160 -0.0403 0.1785 0.7387
3.000 0.4862 0.02029 0.01191 -0.0390 0.1594 0.7408
3.250 0.5074 0.02073 0.01223 -0.0380 0.1464 0.7432
3.500 0.5313 0.02105 0.01249 -0.0375 0.1359 0.7460
3.750 0.5557 0.02145 0.01281 -0.0372 0.1270 0.7495
4.000 0.5818 0.02194 0.01317 -0.0375 0.1195 0.7533
4.250 0.6104 0.02234 0.01347 -0.0383 0.1129 0.7564
4.500 0.6325 0.02280 0.01390 -0.0373 0.1079 0.7584
4.750 0.6556 0.02324 0.01429 -0.0365 0.1036 0.7606
5.000 0.6801 0.02388 0.01486 -0.0360 0.1000 0.7630
5.250 0.7057 0.02435 0.01534 -0.0356 0.0966 0.7658
5.500 0.7326 0.02493 0.01581 -0.0357 0.0938 0.7693
5.750 0.7622 0.02564 0.01649 -0.0363 0.0912 0.7731
6.000 0.7933 0.02622 0.01707 -0.0373 0.0887 0.7767
6.250 0.8184 0.02674 0.01758 -0.0368 0.0869 0.7789
6.500 0.8457 0.02748 0.01824 -0.0367 0.0854 0.7814
6.750 0.8739 0.02839 0.01917 -0.0368 0.0841 0.7842
7.000 0.9005 0.02915 0.02005 -0.0366 0.0828 0.7874
7.250 0.9286 0.03001 0.02098 -0.0368 0.0817 0.7909
7.500 0.9583 0.03095 0.02196 -0.0375 0.0806 0.7950
7.750 0.9844 0.03182 0.02288 -0.0373 0.0797 0.7982
8.000 1.0086 0.03270 0.02380 -0.0368 0.0789 0.8013
8.250 1.0346 0.03374 0.02484 -0.0367 0.0780 0.8047
8.500 1.0617 0.03527 0.02640 -0.0370 0.0772 0.8083
8.750 1.0829 0.03649 0.02787 -0.0363 0.0766 0.8122
9.000 1.1042 0.03797 0.02957 -0.0358 0.0760 0.8157
9.250 1.1211 0.03953 0.03138 -0.0343 0.0757 0.8188
9.500 1.1369 0.04131 0.03341 -0.0329 0.0754 0.8222
9.750 1.1513 0.04333 0.03568 -0.0316 0.0752 0.8262
10.000 1.1639 0.04564 0.03826 -0.0302 0.0751 0.8305
10.250 1.1720 0.04812 0.04102 -0.0284 0.0751 0.8343
10.500 1.1748 0.05072 0.04391 -0.0258 0.0753 0.8380
10.750 1.1738 0.05363 0.04711 -0.0232 0.0756 0.8421
11.000 1.1687 0.05669 0.05042 -0.0205 0.0759 0.8463
11.250 1.1601 0.05980 0.05377 -0.0178 0.0762 0.8503
11.500 1.1476 0.06293 0.05712 -0.0148 0.0765 0.8539
11.750 1.1355 0.06629 0.06068 -0.0126 0.0767 0.8578
12.000 1.1258 0.06986 0.06441 -0.0111 0.0769 0.8619
12.250 1.1236 0.07349 0.06812 -0.0105 0.0772 0.8659
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