NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 50,000 Max Cl/Cd: 26.82 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0115-il-50000-n5.txt Download as CSV file: xf-nlf0115-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4212 0.11885 0.11126 -0.0512 1.0000 0.0584
-11.750 -0.4198 0.11505 0.10751 -0.0517 1.0000 0.0580
-11.500 -0.4187 0.11136 0.10386 -0.0521 1.0000 0.0573
-11.250 -0.4201 0.10735 0.09991 -0.0529 1.0000 0.0564
-11.000 -0.4259 0.10263 0.09525 -0.0545 1.0000 0.0557
-10.750 -0.4339 0.09750 0.09018 -0.0565 1.0000 0.0548
-10.500 -0.4479 0.09196 0.08471 -0.0588 1.0000 0.0536
-10.250 -0.4677 0.08670 0.07949 -0.0606 1.0000 0.0526
-10.000 -0.4938 0.08192 0.07472 -0.0613 1.0000 0.0517
-9.750 -0.5265 0.07787 0.07064 -0.0604 1.0000 0.0506
-9.250 -0.6238 0.07315 0.06558 -0.0497 1.0000 0.0481
-9.000 -0.6394 0.07094 0.06331 -0.0459 1.0000 0.0480
-8.750 -0.6564 0.06880 0.06107 -0.0418 1.0000 0.0480
-8.500 -0.6685 0.06672 0.05891 -0.0379 1.0000 0.0479
-8.250 -0.6807 0.06461 0.05666 -0.0340 1.0000 0.0478
-8.000 -0.6882 0.06234 0.05422 -0.0307 0.9995 0.0477
-7.750 -0.6713 0.05853 0.05005 -0.0322 0.9914 0.0476
-7.500 -0.6518 0.05507 0.04620 -0.0335 0.9839 0.0474
-7.250 -0.6329 0.05192 0.04263 -0.0341 0.9755 0.0474
-7.000 -0.6118 0.04900 0.03928 -0.0345 0.9680 0.0475
-6.750 -0.5874 0.04634 0.03616 -0.0351 0.9612 0.0477
-6.250 -0.5360 0.04181 0.03110 -0.0361 0.9480 0.0495
-6.000 -0.5083 0.04022 0.02938 -0.0368 0.9420 0.0517
-5.750 -0.4803 0.03871 0.02763 -0.0372 0.9355 0.0542
-5.500 -0.4435 0.03716 0.02581 -0.0385 0.9315 0.0563
-5.250 -0.4104 0.03599 0.02442 -0.0386 0.9263 0.0582
-5.000 -0.3743 0.03497 0.02340 -0.0392 0.9221 0.0607
-4.750 -0.3407 0.03414 0.02252 -0.0401 0.9179 0.0656
-4.500 -0.3172 0.03348 0.02172 -0.0392 0.9116 0.0716
-4.250 -0.2972 0.03263 0.02092 -0.0384 0.9050 0.0782
-4.000 -0.2763 0.03173 0.01997 -0.0377 0.8995 0.0880
-3.750 -0.2659 0.03095 0.01924 -0.0354 0.8918 0.1028
-3.500 -0.2499 0.02947 0.01815 -0.0346 0.8868 0.1497
-3.250 -0.2667 0.02820 0.01979 -0.0248 0.8788 0.5885
-3.000 -0.2605 0.02941 0.02073 -0.0188 0.8725 0.7129
-2.750 -0.2404 0.03177 0.02301 -0.0112 0.8684 0.7822
-2.500 -0.1482 0.03431 0.02511 -0.0155 0.8717 0.8433
-2.250 -0.1474 0.03408 0.02474 -0.0117 0.8636 0.8492
-2.000 -0.1178 0.03387 0.02428 -0.0128 0.8592 0.8521
-1.750 -0.0859 0.03362 0.02381 -0.0144 0.8558 0.8552
-1.500 -0.0899 0.03352 0.02362 -0.0098 0.8477 0.8606
-1.250 -0.0717 0.03329 0.02324 -0.0090 0.8429 0.8643
-1.000 -0.0373 0.03314 0.02289 -0.0109 0.8399 0.8663
-0.750 -0.0333 0.03321 0.02289 -0.0078 0.8323 0.8702
-0.500 -0.0128 0.03312 0.02268 -0.0074 0.8278 0.8735
-0.250 0.0129 0.03297 0.02239 -0.0079 0.8243 0.8763
0.000 0.0116 0.03306 0.02245 -0.0039 0.8166 0.8807
0.250 0.0367 0.03310 0.02240 -0.0043 0.8122 0.8833
0.500 0.0674 0.03308 0.02228 -0.0055 0.8088 0.8855
0.750 0.0708 0.03326 0.02243 -0.0025 0.8015 0.8897
1.000 0.0887 0.03329 0.02240 -0.0016 0.7962 0.8936
1.250 0.1215 0.03332 0.02238 -0.0031 0.7928 0.8959
1.500 0.1319 0.03366 0.02271 -0.0013 0.7852 0.8997
1.750 0.1581 0.03378 0.02281 -0.0018 0.7799 0.9025
2.000 0.1934 0.03379 0.02280 -0.0036 0.7763 0.9050
2.250 0.1967 0.03418 0.02320 -0.0007 0.7669 0.9107
2.500 0.2338 0.03426 0.02329 -0.0028 0.7621 0.9132
2.750 0.2527 0.03462 0.02368 -0.0023 0.7535 0.9177
3.000 0.2857 0.03465 0.02374 -0.0036 0.7470 0.9212
3.250 0.3067 0.03484 0.02398 -0.0032 0.7376 0.9259
3.500 0.3502 0.03456 0.02375 -0.0057 0.7301 0.9280
3.750 0.3773 0.03460 0.02385 -0.0060 0.7178 0.9323
4.000 0.4138 0.03424 0.02356 -0.0072 0.7071 0.9363
4.250 0.4613 0.03341 0.02282 -0.0094 0.6976 0.9392
4.500 0.4921 0.03323 0.02275 -0.0100 0.6840 0.9441
4.750 0.5257 0.03293 0.02256 -0.0109 0.6706 0.9492
5.000 0.5599 0.03247 0.02224 -0.0116 0.6573 0.9550
5.250 0.5988 0.03189 0.02179 -0.0130 0.6431 0.9596
5.500 0.6326 0.03138 0.02142 -0.0137 0.6269 0.9664
5.750 0.6634 0.03093 0.02114 -0.0141 0.6083 0.9749
6.000 0.6952 0.03034 0.02070 -0.0145 0.5880 0.9860
6.250 0.6945 0.03041 0.02085 -0.0107 0.5657 1.0000
6.500 0.6911 0.03046 0.02092 -0.0062 0.5424 1.0000
6.750 0.6977 0.03054 0.02106 -0.0034 0.5130 1.0000
7.000 0.7207 0.02997 0.02046 -0.0020 0.4793 1.0000
7.250 0.7521 0.02912 0.01940 -0.0011 0.4363 1.0000
7.500 0.7773 0.02898 0.01889 0.0001 0.3922 1.0000
7.750 0.7933 0.02961 0.01917 0.0017 0.3573 1.0000
8.000 0.8060 0.03056 0.01988 0.0032 0.3295 1.0000
8.250 0.8194 0.03158 0.02069 0.0045 0.3074 1.0000
8.500 0.8340 0.03263 0.02163 0.0057 0.2883 1.0000
8.750 0.8499 0.03368 0.02260 0.0066 0.2716 1.0000
9.000 0.8675 0.03470 0.02356 0.0073 0.2571 1.0000
9.250 0.8871 0.03569 0.02449 0.0078 0.2442 1.0000
9.500 0.9076 0.03668 0.02543 0.0083 0.2322 1.0000
9.750 0.9275 0.03773 0.02659 0.0087 0.2208 1.0000
10.000 0.9507 0.03875 0.02765 0.0088 0.2109 1.0000
10.250 0.9758 0.03971 0.02858 0.0088 0.2014 1.0000
10.500 0.9940 0.04097 0.03004 0.0093 0.1925 1.0000
10.750 1.0203 0.04203 0.03107 0.0091 0.1847 1.0000
11.000 1.0353 0.04348 0.03276 0.0098 0.1770 1.0000
11.250 1.0596 0.04462 0.03385 0.0097 0.1702 1.0000
11.500 1.0695 0.04638 0.03593 0.0109 0.1638 1.0000
11.750 1.0883 0.04776 0.03738 0.0112 0.1581 1.0000
12.000 1.0993 0.04958 0.03939 0.0121 0.1527 1.0000
12.250 1.1050 0.05156 0.04161 0.0133 0.1476 1.0000
12.500 1.1224 0.05304 0.04312 0.0137 0.1429 1.0000
12.750 1.1251 0.05543 0.04576 0.0149 0.1390 1.0000
13.000 1.1190 0.05827 0.04891 0.0163 0.1353 1.0000
13.250 1.1201 0.06064 0.05148 0.0172 0.1315 1.0000
13.500 1.1407 0.06192 0.05267 0.0174 0.1274 1.0000
13.750 1.1192 0.06611 0.05726 0.0186 0.1255 1.0000
14.000 1.0960 0.07088 0.06235 0.0191 0.1237 1.0000
14.250 1.0678 0.07652 0.06829 0.0187 0.1222 1.0000
14.500 1.0301 0.08384 0.07585 0.0171 0.1213 1.0000
14.750 0.9557 0.09766 0.08988 0.0112 0.1218 1.0000
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Polar data table (+)
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