NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: NASA/LANGLEY NLF(1)-0215F AIRFOIL (nlf0215f-il) Reynolds number: 500,000 Max Cl/Cd: 108.86 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0215f-il-500000-n5.txt Download as CSV file: xf-nlf0215f-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(1)-0215F AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2444 0.07858 0.07610 -0.0907 0.9271 0.0106
-10.000 -0.2442 0.06419 0.06166 -0.1074 0.9162 0.0105
-9.500 -0.2988 0.03221 0.02816 -0.1416 0.8404 0.0104
-9.250 -0.3030 0.02940 0.02490 -0.1402 0.8134 0.0105
-9.000 -0.3015 0.02694 0.02203 -0.1384 0.7935 0.0105
-8.750 -0.2935 0.02487 0.01955 -0.1369 0.7782 0.0107
-8.500 -0.2792 0.02345 0.01783 -0.1358 0.7653 0.0107
-8.250 -0.2623 0.02220 0.01631 -0.1350 0.7544 0.0108
-8.000 -0.2447 0.02081 0.01465 -0.1341 0.7446 0.0109
-7.750 -0.2258 0.01943 0.01309 -0.1334 0.7355 0.0111
-7.500 -0.2042 0.01863 0.01214 -0.1329 0.7274 0.0113
-7.250 -0.1813 0.01803 0.01144 -0.1326 0.7193 0.0116
-7.000 -0.1582 0.01742 0.01071 -0.1321 0.7121 0.0118
-6.750 -0.1345 0.01680 0.00998 -0.1318 0.7049 0.0122
-6.500 -0.1109 0.01618 0.00923 -0.1313 0.6987 0.0124
-6.250 -0.0867 0.01554 0.00850 -0.1310 0.6932 0.0126
-6.000 -0.0622 0.01499 0.00786 -0.1306 0.6877 0.0128
-5.750 -0.0377 0.01448 0.00726 -0.1303 0.6826 0.0131
-5.500 -0.0124 0.01402 0.00673 -0.1301 0.6781 0.0134
-5.250 0.0133 0.01360 0.00626 -0.1300 0.6732 0.0137
-5.000 0.0392 0.01324 0.00583 -0.1300 0.6685 0.0140
-4.750 0.0653 0.01282 0.00536 -0.1300 0.6643 0.0143
-4.500 0.0923 0.01240 0.00492 -0.1303 0.6602 0.0148
-4.250 0.1198 0.01211 0.00460 -0.1306 0.6563 0.0154
-4.000 0.1475 0.01187 0.00433 -0.1308 0.6526 0.0161
-3.500 0.2039 0.01146 0.00384 -0.1315 0.6461 0.0182
-3.250 0.2325 0.01123 0.00360 -0.1320 0.6425 0.0195
-3.000 0.2612 0.01107 0.00340 -0.1323 0.6390 0.0212
-2.750 0.2899 0.01092 0.00323 -0.1328 0.6358 0.0244
-2.250 0.3495 0.01034 0.00292 -0.1345 0.6304 0.1063
-2.000 0.3818 0.00972 0.00276 -0.1363 0.6273 0.2435
-1.750 0.4209 0.00841 0.00261 -0.1405 0.6242 0.5912
-1.500 0.4484 0.00868 0.00296 -0.1402 0.6214 0.6600
-1.250 0.4753 0.00910 0.00336 -0.1397 0.6189 0.6868
-1.000 0.5009 0.00954 0.00380 -0.1387 0.6163 0.7019
-0.750 0.5293 0.00972 0.00395 -0.1387 0.6137 0.7096
-0.500 0.5586 0.00974 0.00392 -0.1392 0.6110 0.7114
-0.250 0.5869 0.00977 0.00392 -0.1393 0.6083 0.7124
0.000 0.6152 0.00981 0.00392 -0.1395 0.6055 0.7133
0.250 0.6437 0.00986 0.00393 -0.1397 0.6030 0.7140
0.500 0.6723 0.00992 0.00394 -0.1400 0.6007 0.7149
0.750 0.7009 0.00994 0.00397 -0.1403 0.5983 0.7157
1.000 0.7296 0.00996 0.00399 -0.1406 0.5955 0.7164
1.250 0.7581 0.01000 0.00402 -0.1408 0.5928 0.7172
1.500 0.7865 0.01005 0.00405 -0.1411 0.5901 0.7181
1.750 0.8149 0.01011 0.00408 -0.1414 0.5874 0.7188
2.000 0.8434 0.01018 0.00412 -0.1417 0.5848 0.7195
2.250 0.8717 0.01020 0.00417 -0.1419 0.5816 0.7202
2.500 0.8996 0.01024 0.00422 -0.1421 0.5776 0.7210
2.750 0.9272 0.01029 0.00427 -0.1422 0.5731 0.7220
3.000 0.9545 0.01037 0.00431 -0.1422 0.5682 0.7227
3.250 0.9819 0.01039 0.00436 -0.1423 0.5623 0.7233
3.500 1.0089 0.01045 0.00442 -0.1423 0.5567 0.7239
3.750 1.0359 0.01053 0.00449 -0.1423 0.5516 0.7245
4.000 1.0627 0.01057 0.00456 -0.1422 0.5445 0.7251
4.250 1.0886 0.01067 0.00463 -0.1420 0.5376 0.7257
4.500 1.1154 0.01073 0.00473 -0.1420 0.5301 0.7264
4.750 1.1406 0.01083 0.00482 -0.1416 0.5223 0.7270
5.000 1.1663 0.01090 0.00493 -0.1413 0.5126 0.7276
5.250 1.1908 0.01102 0.00506 -0.1408 0.5018 0.7281
5.500 1.2143 0.01117 0.00520 -0.1401 0.4879 0.7286
5.750 1.2366 0.01136 0.00536 -0.1392 0.4696 0.7291
6.000 1.2562 0.01167 0.00558 -0.1378 0.4464 0.7296
6.250 1.2742 0.01205 0.00586 -0.1361 0.4188 0.7302
6.500 1.2892 0.01258 0.00624 -0.1340 0.3866 0.7308
6.750 1.3002 0.01320 0.00670 -0.1311 0.3514 0.7314
7.000 1.3099 0.01386 0.00721 -0.1279 0.3186 0.7321
7.250 1.3203 0.01455 0.00777 -0.1251 0.2893 0.7328
7.500 1.3307 0.01526 0.00836 -0.1223 0.2626 0.7334
7.750 1.3416 0.01596 0.00896 -0.1196 0.2383 0.7341
8.250 1.3624 0.01743 0.01027 -0.1144 0.1983 0.7358
8.500 1.3722 0.01821 0.01098 -0.1118 0.1801 0.7367
8.750 1.3814 0.01904 0.01176 -0.1092 0.1636 0.7375
9.000 1.3908 0.01990 0.01258 -0.1068 0.1498 0.7382
9.250 1.4001 0.02080 0.01345 -0.1045 0.1378 0.7389
9.500 1.4092 0.02176 0.01440 -0.1023 0.1278 0.7396
9.750 1.4185 0.02275 0.01539 -0.1002 0.1183 0.7403
10.000 1.4276 0.02381 0.01644 -0.0983 0.1096 0.7410
10.250 1.4352 0.02502 0.01765 -0.0963 0.1014 0.7416
10.750 1.4523 0.02749 0.02017 -0.0930 0.0882 0.7428
11.000 1.4609 0.02880 0.02151 -0.0915 0.0823 0.7435
11.250 1.4680 0.03029 0.02302 -0.0900 0.0770 0.7441
11.500 1.4766 0.03170 0.02449 -0.0887 0.0719 0.7448
11.750 1.4823 0.03341 0.02621 -0.0873 0.0666 0.7455
12.000 1.4909 0.03493 0.02779 -0.0862 0.0627 0.7461
12.250 1.4970 0.03671 0.02959 -0.0851 0.0581 0.7468
12.500 1.5037 0.03848 0.03141 -0.0841 0.0541 0.7476
12.750 1.5102 0.04032 0.03328 -0.0832 0.0500 0.7483
13.000 1.5153 0.04235 0.03534 -0.0823 0.0463 0.7490
13.250 1.5226 0.04419 0.03725 -0.0816 0.0433 0.7498
13.500 1.5283 0.04624 0.03933 -0.0809 0.0403 0.7505
13.750 1.5336 0.04838 0.04153 -0.0802 0.0381 0.7514
14.000 1.5406 0.05038 0.04361 -0.0797 0.0363 0.7523
14.250 1.5465 0.05254 0.04583 -0.0792 0.0343 0.7532
14.500 1.5510 0.05489 0.04824 -0.0788 0.0324 0.7541
14.750 1.5563 0.05722 0.05063 -0.0785 0.0307 0.7550
15.000 1.5619 0.05954 0.05302 -0.0782 0.0291 0.7558
15.250 1.5662 0.06207 0.05562 -0.0781 0.0273 0.7566
15.500 1.5693 0.06478 0.05838 -0.0780 0.0256 0.7572
15.750 1.5738 0.06737 0.06107 -0.0779 0.0242 0.7580
16.000 1.5776 0.07008 0.06386 -0.0780 0.0226 0.7587
16.250 1.5797 0.07307 0.06692 -0.0781 0.0210 0.7595
16.500 1.5821 0.07609 0.07003 -0.0784 0.0198 0.7603
16.750 1.5849 0.07907 0.07311 -0.0787 0.0184 0.7611
17.000 1.5857 0.08239 0.07651 -0.0791 0.0171 0.7619
17.250 1.5862 0.08581 0.08001 -0.0797 0.0159 0.7627
17.500 1.5871 0.08922 0.08352 -0.0803 0.0147 0.7636
17.750 1.5859 0.09300 0.08738 -0.0812 0.0135 0.7644
18.000 1.5845 0.09688 0.09137 -0.0821 0.0125 0.7653
18.250 1.5832 0.10077 0.09536 -0.0831 0.0116 0.7662
18.500 1.5804 0.10495 0.09963 -0.0844 0.0108 0.7670
18.750 1.5762 0.10942 0.10420 -0.0858 0.0101 0.7679
19.000 1.5732 0.11375 0.10865 -0.0874 0.0096 0.7688
19.250 1.5695 0.11827 0.11328 -0.0891 0.0091 0.7697
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Polar data table (+)
Polar graphs
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