NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7301 AIRFOIL (nlr7301-il) Reynolds number: 200,000 Max Cl/Cd: 37.21 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlr7301-il-200000-n5.txt Download as CSV file: xf-nlr7301-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.9636 0.09841 0.09250 -0.0489 1.0000 0.0390
-17.500 -0.9886 0.09026 0.08410 -0.0537 1.0000 0.0392
-17.250 -0.9929 0.08596 0.07974 -0.0560 1.0000 0.0394
-17.000 -0.9977 0.08167 0.07536 -0.0582 1.0000 0.0397
-16.750 -1.0020 0.07755 0.07114 -0.0602 1.0000 0.0400
-16.500 -1.0063 0.07353 0.06702 -0.0621 1.0000 0.0402
-16.250 -1.0101 0.06973 0.06311 -0.0638 1.0000 0.0406
-16.000 -1.0129 0.06616 0.05941 -0.0652 1.0000 0.0409
-15.750 -1.0147 0.06283 0.05596 -0.0665 1.0000 0.0413
-15.500 -1.0153 0.05975 0.05275 -0.0674 1.0000 0.0416
-15.250 -1.0146 0.05688 0.04974 -0.0682 1.0000 0.0420
-15.000 -1.0130 0.05421 0.04691 -0.0687 1.0000 0.0425
-14.750 -1.0102 0.05175 0.04431 -0.0691 1.0000 0.0429
-14.500 -1.0065 0.04944 0.04183 -0.0693 1.0000 0.0434
-14.250 -0.9973 0.04776 0.04012 -0.0692 1.0000 0.0438
-14.000 -0.9878 0.04615 0.03851 -0.0692 1.0000 0.0442
-13.750 -0.9781 0.04459 0.03692 -0.0692 1.0000 0.0447
-13.500 -0.9683 0.04306 0.03535 -0.0691 1.0000 0.0453
-13.250 -0.9580 0.04158 0.03382 -0.0689 1.0000 0.0460
-13.000 -0.9472 0.04016 0.03232 -0.0686 1.0000 0.0467
-12.750 -0.9360 0.03879 0.03084 -0.0683 1.0000 0.0475
-12.500 -0.9240 0.03752 0.02948 -0.0678 1.0000 0.0483
-12.250 -0.9116 0.03640 0.02839 -0.0673 1.0000 0.0489
-12.000 -0.8998 0.03533 0.02733 -0.0667 1.0000 0.0495
-11.750 -0.8889 0.03434 0.02633 -0.0658 1.0000 0.0502
-11.500 -0.8813 0.03347 0.02545 -0.0642 1.0000 0.0510
-11.250 -0.8753 0.03268 0.02463 -0.0622 0.9985 0.0517
-11.000 -0.8507 0.03163 0.02348 -0.0635 0.9934 0.0530
-10.750 -0.8274 0.03058 0.02245 -0.0647 0.9874 0.0540
-10.500 -0.8026 0.02960 0.02147 -0.0661 0.9821 0.0553
-10.250 -0.7779 0.02868 0.02052 -0.0672 0.9767 0.0568
-10.000 -0.7542 0.02783 0.01959 -0.0679 0.9708 0.0584
-9.750 -0.7298 0.02691 0.01871 -0.0689 0.9662 0.0598
-9.500 -0.7090 0.02613 0.01792 -0.0691 0.9597 0.0613
-9.250 -0.6866 0.02538 0.01714 -0.0695 0.9540 0.0631
-9.000 -0.6630 0.02460 0.01635 -0.0700 0.9496 0.0651
-8.750 -0.6455 0.02393 0.01570 -0.0694 0.9424 0.0669
-8.500 -0.6251 0.02329 0.01503 -0.0692 0.9365 0.0693
-8.250 -0.6048 0.02263 0.01435 -0.0689 0.9319 0.0716
-8.000 -0.5873 0.02206 0.01379 -0.0683 0.9257 0.0739
-7.750 -0.5663 0.02151 0.01321 -0.0681 0.9207 0.0770
-7.500 -0.5448 0.02088 0.01261 -0.0681 0.9164 0.0800
-7.250 -0.5211 0.02034 0.01206 -0.0682 0.9132 0.0839
-7.000 -0.5000 0.01981 0.01157 -0.0681 0.9085 0.0875
-6.750 -0.4774 0.01937 0.01111 -0.0679 0.9037 0.0922
-6.500 -0.4542 0.01887 0.01066 -0.0679 0.8995 0.0972
-6.250 -0.4296 0.01842 0.01022 -0.0679 0.8961 0.1032
-6.000 -0.4041 0.01799 0.00981 -0.0680 0.8934 0.1104
-5.750 -0.3792 0.01756 0.00943 -0.0682 0.8904 0.1187
-5.500 -0.3554 0.01718 0.00912 -0.0681 0.8864 0.1284
-5.250 -0.3306 0.01677 0.00879 -0.0682 0.8826 0.1409
-5.000 -0.3048 0.01634 0.00844 -0.0684 0.8790 0.1580
-4.750 -0.2785 0.01581 0.00807 -0.0688 0.8758 0.1832
-4.500 -0.2515 0.01520 0.00767 -0.0694 0.8733 0.2239
-4.250 -0.2240 0.01440 0.00721 -0.0705 0.8711 0.2895
-4.000 -0.1972 0.01353 0.00684 -0.0716 0.8684 0.3863
-3.750 -0.1711 0.01320 0.00702 -0.0717 0.8645 0.4817
-3.500 -0.1429 0.01324 0.00718 -0.0716 0.8610 0.5228
-3.250 -0.1139 0.01331 0.00729 -0.0716 0.8580 0.5454
-3.000 -0.0840 0.01336 0.00732 -0.0718 0.8555 0.5622
-2.750 -0.0547 0.01347 0.00746 -0.0717 0.8530 0.5746
-2.500 -0.0243 0.01351 0.00749 -0.0719 0.8507 0.5853
-2.250 0.0056 0.01362 0.00761 -0.0719 0.8487 0.5946
-2.000 0.0339 0.01381 0.00781 -0.0718 0.8454 0.6059
-1.750 0.0604 0.01418 0.00825 -0.0711 0.8412 0.6209
-1.500 0.0861 0.01456 0.00872 -0.0698 0.8363 0.6314
-1.250 0.1158 0.01453 0.00868 -0.0693 0.8298 0.6389
-1.000 0.1456 0.01425 0.00831 -0.0692 0.8196 0.6442
-0.750 0.1743 0.01395 0.00798 -0.0686 0.8072 0.6468
-0.500 0.2008 0.01372 0.00774 -0.0675 0.7906 0.6489
-0.250 0.2280 0.01348 0.00746 -0.0665 0.7700 0.6512
0.000 0.2558 0.01333 0.00727 -0.0659 0.7507 0.6537
0.250 0.2844 0.01322 0.00712 -0.0656 0.7344 0.6562
0.500 0.3126 0.01312 0.00698 -0.0653 0.7120 0.6591
0.750 0.3409 0.01303 0.00676 -0.0650 0.6741 0.6623
1.000 0.3646 0.01320 0.00637 -0.0636 0.5666 0.6654
1.250 0.3770 0.01422 0.00654 -0.0609 0.4122 0.6678
1.500 0.3908 0.01525 0.00695 -0.0587 0.2890 0.6696
1.750 0.4096 0.01601 0.00729 -0.0573 0.2098 0.6715
2.000 0.4320 0.01653 0.00758 -0.0564 0.1681 0.6738
2.250 0.4560 0.01694 0.00783 -0.0558 0.1454 0.6763
2.500 0.4811 0.01726 0.00806 -0.0554 0.1312 0.6789
2.750 0.5066 0.01757 0.00828 -0.0550 0.1209 0.6815
3.000 0.5326 0.01785 0.00850 -0.0548 0.1129 0.6843
3.250 0.5589 0.01814 0.00872 -0.0546 0.1062 0.6871
3.500 0.5849 0.01846 0.00895 -0.0545 0.1005 0.6899
3.750 0.6092 0.01877 0.00926 -0.0538 0.0952 0.6920
4.000 0.6330 0.01912 0.00960 -0.0530 0.0909 0.6942
4.250 0.6572 0.01947 0.00994 -0.0524 0.0867 0.6966
4.500 0.6810 0.01986 0.01030 -0.0517 0.0834 0.6991
4.750 0.7053 0.02022 0.01066 -0.0511 0.0802 0.7018
5.000 0.7290 0.02065 0.01104 -0.0505 0.0776 0.7046
5.250 0.7533 0.02105 0.01144 -0.0500 0.0751 0.7076
5.500 0.7776 0.02148 0.01185 -0.0496 0.0728 0.7107
5.750 0.8006 0.02194 0.01227 -0.0490 0.0710 0.7133
6.000 0.8226 0.02241 0.01277 -0.0480 0.0692 0.7156
6.250 0.8444 0.02288 0.01328 -0.0470 0.0674 0.7181
6.500 0.8656 0.02335 0.01375 -0.0460 0.0660 0.7210
6.750 0.8862 0.02387 0.01425 -0.0449 0.0648 0.7241
7.000 0.9074 0.02441 0.01482 -0.0440 0.0636 0.7272
7.250 0.9291 0.02497 0.01541 -0.0432 0.0625 0.7304
7.500 0.9512 0.02558 0.01601 -0.0425 0.0615 0.7336
7.750 0.9723 0.02618 0.01664 -0.0416 0.0606 0.7361
8.000 0.9926 0.02680 0.01728 -0.0406 0.0599 0.7386
8.250 1.0126 0.02746 0.01795 -0.0396 0.0593 0.7412
8.500 1.0326 0.02820 0.01868 -0.0387 0.0587 0.7442
8.750 1.0534 0.02894 0.01950 -0.0378 0.0581 0.7475
9.000 1.0742 0.02972 0.02035 -0.0370 0.0574 0.7512
9.250 1.0949 0.03053 0.02121 -0.0363 0.0568 0.7549
9.500 1.1142 0.03135 0.02210 -0.0353 0.0563 0.7578
9.750 1.1327 0.03218 0.02300 -0.0342 0.0558 0.7606
10.000 1.1508 0.03302 0.02391 -0.0332 0.0553 0.7635
10.250 1.1684 0.03389 0.02483 -0.0321 0.0548 0.7668
10.500 1.1858 0.03478 0.02575 -0.0311 0.0544 0.7702
10.750 1.2030 0.03571 0.02669 -0.0302 0.0540 0.7737
11.000 1.2201 0.03670 0.02768 -0.0293 0.0536 0.7770
11.250 1.2353 0.03778 0.02886 -0.0281 0.0532 0.7798
11.500 1.2486 0.03900 0.03024 -0.0268 0.0529 0.7831
11.750 1.2613 0.04031 0.03171 -0.0255 0.0525 0.7868
12.000 1.2731 0.04172 0.03327 -0.0242 0.0522 0.7908
12.250 1.2839 0.04324 0.03492 -0.0230 0.0519 0.7946
12.500 1.2929 0.04482 0.03666 -0.0217 0.0516 0.7978
12.750 1.3001 0.04651 0.03851 -0.0203 0.0513 0.8009
13.000 1.3060 0.04833 0.04049 -0.0190 0.0511 0.8043
13.250 1.3104 0.05031 0.04263 -0.0178 0.0508 0.8080
13.500 1.3134 0.05246 0.04494 -0.0167 0.0506 0.8120
13.750 1.3145 0.05479 0.04743 -0.0157 0.0504 0.8158
14.000 1.3131 0.05731 0.05014 -0.0147 0.0502 0.8192
14.250 1.3100 0.06010 0.05311 -0.0139 0.0501 0.8229
14.500 1.3047 0.06324 0.05643 -0.0135 0.0499 0.8268
14.750 1.2969 0.06678 0.06016 -0.0134 0.0498 0.8305
15.000 1.2857 0.07084 0.06442 -0.0137 0.0497 0.8339
15.250 1.2697 0.07564 0.06945 -0.0146 0.0496 0.8372
15.500 1.2482 0.08163 0.07569 -0.0166 0.0495 0.8405
15.750 1.2133 0.09037 0.08477 -0.0208 0.0495 0.8432
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