NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-1T AIRFOIL (nlr1t-il) Reynolds number: 200,000 Max Cl/Cd: 52.02 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlr1t-il-200000-n5.txt Download as CSV file: xf-nlr1t-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLR-1T 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5321 0.10647 0.10288 -0.0115 1.0000 0.0260
-9.750 -0.5319 0.10192 0.09836 -0.0146 1.0000 0.0268
-7.750 -0.5855 0.06234 0.05862 -0.0307 1.0000 0.0201
-7.500 -0.5803 0.05816 0.05430 -0.0313 0.9960 0.0197
-6.750 -0.5411 0.04422 0.03948 -0.0332 0.9836 0.0197
-6.500 -0.5264 0.04047 0.03545 -0.0328 0.9796 0.0192
-6.250 -0.5085 0.03672 0.03134 -0.0324 0.9766 0.0186
-6.000 -0.4882 0.03316 0.02738 -0.0319 0.9744 0.0182
-5.750 -0.4694 0.03014 0.02395 -0.0306 0.9714 0.0179
-5.500 -0.4493 0.02752 0.02091 -0.0293 0.9685 0.0178
-5.250 -0.4263 0.02525 0.01825 -0.0284 0.9662 0.0179
-5.000 -0.4009 0.02332 0.01598 -0.0278 0.9645 0.0181
-4.750 -0.3735 0.02176 0.01412 -0.0277 0.9630 0.0186
-4.500 -0.3447 0.02074 0.01283 -0.0278 0.9617 0.0199
-4.250 -0.3158 0.01970 0.01158 -0.0280 0.9607 0.0204
-4.000 -0.2924 0.01869 0.01043 -0.0270 0.9585 0.0205
-3.750 -0.2680 0.01780 0.00944 -0.0263 0.9564 0.0206
-3.500 -0.2436 0.01676 0.00837 -0.0256 0.9547 0.0210
-3.250 -0.2189 0.01593 0.00752 -0.0251 0.9529 0.0216
-3.000 -0.1929 0.01529 0.00687 -0.0249 0.9511 0.0225
-2.750 -0.1662 0.01482 0.00636 -0.0248 0.9496 0.0236
-2.500 -0.1389 0.01443 0.00593 -0.0247 0.9483 0.0251
-2.250 -0.1106 0.01417 0.00561 -0.0249 0.9472 0.0282
-2.000 -0.0852 0.01384 0.00527 -0.0245 0.9451 0.0328
-1.750 -0.0616 0.01359 0.00499 -0.0236 0.9410 0.0410
-1.500 -0.0368 0.01279 0.00472 -0.0233 0.9375 0.1679
-1.250 0.0626 0.01063 0.00543 -0.0368 0.9461 0.9660
-1.000 0.1084 0.01052 0.00519 -0.0400 0.9357 0.9782
-0.750 0.1461 0.01023 0.00477 -0.0410 0.9164 0.9858
-0.500 0.1811 0.01000 0.00441 -0.0419 0.8950 0.9930
-0.250 0.2182 0.00986 0.00419 -0.0437 0.8840 0.9984
0.000 0.2455 0.00976 0.00402 -0.0435 0.8750 1.0000
0.250 0.2690 0.00969 0.00391 -0.0426 0.8635 1.0000
0.500 0.2926 0.00962 0.00379 -0.0416 0.8507 1.0000
0.750 0.3163 0.00955 0.00369 -0.0406 0.8367 1.0000
1.000 0.3401 0.00947 0.00358 -0.0396 0.8195 1.0000
1.250 0.3638 0.00941 0.00350 -0.0386 0.7927 1.0000
1.500 0.3848 0.00930 0.00306 -0.0363 0.6919 1.0000
1.750 0.4045 0.00983 0.00287 -0.0342 0.5635 1.0000
2.000 0.4259 0.01044 0.00300 -0.0331 0.4648 1.0000
2.250 0.4478 0.01099 0.00316 -0.0322 0.3867 1.0000
2.500 0.4702 0.01146 0.00333 -0.0314 0.3252 1.0000
2.750 0.4930 0.01186 0.00350 -0.0306 0.2812 1.0000
3.000 0.5162 0.01220 0.00370 -0.0299 0.2524 1.0000
3.250 0.5396 0.01250 0.00390 -0.0292 0.2330 1.0000
3.500 0.5631 0.01278 0.00412 -0.0285 0.2189 1.0000
3.750 0.5864 0.01307 0.00436 -0.0277 0.2079 1.0000
4.250 0.6330 0.01365 0.00488 -0.0262 0.1885 1.0000
4.500 0.6562 0.01394 0.00514 -0.0254 0.1793 1.0000
4.750 0.6792 0.01423 0.00541 -0.0246 0.1709 1.0000
5.000 0.7025 0.01449 0.00571 -0.0238 0.1620 1.0000
5.250 0.7251 0.01482 0.00600 -0.0230 0.1547 1.0000
5.500 0.7485 0.01505 0.00631 -0.0222 0.1475 1.0000
5.750 0.7711 0.01537 0.00662 -0.0213 0.1394 1.0000
6.000 0.7942 0.01562 0.00693 -0.0205 0.1300 1.0000
6.250 0.8171 0.01590 0.00729 -0.0197 0.1203 1.0000
6.500 0.8399 0.01618 0.00761 -0.0188 0.1071 1.0000
6.750 0.8619 0.01657 0.00794 -0.0179 0.0883 1.0000
7.000 0.8827 0.01713 0.00842 -0.0168 0.0732 1.0000
7.250 0.9028 0.01777 0.00905 -0.0156 0.0635 1.0000
7.500 0.9233 0.01834 0.00968 -0.0143 0.0580 1.0000
7.750 0.9430 0.01900 0.01037 -0.0131 0.0537 1.0000
8.000 0.9618 0.01973 0.01115 -0.0116 0.0509 1.0000
8.250 0.9813 0.02036 0.01191 -0.0103 0.0492 1.0000
8.500 1.0001 0.02105 0.01272 -0.0088 0.0475 1.0000
8.750 1.0183 0.02179 0.01360 -0.0073 0.0459 1.0000
9.000 1.0360 0.02258 0.01450 -0.0057 0.0446 1.0000
9.250 1.0527 0.02345 0.01546 -0.0041 0.0431 1.0000
9.500 1.0661 0.02470 0.01673 -0.0021 0.0405 1.0000
9.750 1.0855 0.02513 0.01736 -0.0009 0.0384 1.0000
10.000 1.1033 0.02569 0.01808 0.0005 0.0356 1.0000
10.250 1.1196 0.02638 0.01890 0.0021 0.0334 1.0000
10.500 1.1332 0.02727 0.01987 0.0039 0.0314 1.0000
10.750 1.1461 0.02826 0.02100 0.0058 0.0297 1.0000
11.000 1.1620 0.02895 0.02190 0.0074 0.0278 1.0000
11.250 1.1762 0.02970 0.02283 0.0091 0.0257 1.0000
11.500 1.1898 0.03038 0.02363 0.0108 0.0233 1.0000
11.750 1.1995 0.03132 0.02470 0.0131 0.0210 1.0000
12.000 1.2108 0.03213 0.02569 0.0151 0.0178 1.0000
12.250 1.2188 0.03319 0.02686 0.0173 0.0154 1.0000
12.500 1.2238 0.03455 0.02839 0.0197 0.0133 1.0000
12.750 1.2266 0.03613 0.03007 0.0219 0.0121 1.0000
13.000 1.2251 0.03812 0.03223 0.0243 0.0113 1.0000
13.250 1.2216 0.04037 0.03468 0.0263 0.0106 1.0000
13.500 1.2162 0.04296 0.03746 0.0279 0.0102 1.0000
13.750 1.2084 0.04598 0.04068 0.0290 0.0098 1.0000
14.000 1.1977 0.04964 0.04453 0.0292 0.0096 1.0000
14.250 1.1837 0.05428 0.04938 0.0280 0.0094 1.0000
14.500 1.1655 0.06052 0.05584 0.0248 0.0094 1.0000
14.750 1.1417 0.06922 0.06480 0.0190 0.0095 1.0000
15.000 1.1105 0.08043 0.07625 0.0117 0.0099 1.0000
15.250 1.0745 0.09227 0.08826 0.0050 0.0104 1.0000
15.500 1.0386 0.10364 0.09976 -0.0009 0.0110 1.0000
15.750 1.0057 0.11440 0.11060 -0.0063 0.0115 1.0000
16.000 0.9750 0.12497 0.12125 -0.0116 0.0120 1.0000
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Polar data table (+)
Polar graphs
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