NLR-1T AIRFOIL (nlr1t-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-1T AIRFOIL (nlr1t-il) Reynolds number: 200,000 Max Cl/Cd: 53.41 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlr1t-il-200000.txt Download as CSV file: xf-nlr1t-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5471 0.08498 0.08152 -0.0344 1.0000 0.0417
-8.500 -0.5563 0.08130 0.07775 -0.0359 1.0000 0.0419
-8.250 -0.5638 0.07816 0.07450 -0.0357 1.0000 0.0420
-8.000 -0.5744 0.07572 0.07196 -0.0332 1.0000 0.0421
-7.750 -0.5893 0.06931 0.06561 -0.0308 1.0000 0.0428
-7.500 -0.5902 0.06619 0.06255 -0.0282 1.0000 0.0436
-7.250 -0.5925 0.06392 0.06030 -0.0252 1.0000 0.0444
-7.000 -0.5947 0.06164 0.05800 -0.0223 1.0000 0.0454
-6.750 -0.5959 0.05921 0.05549 -0.0197 1.0000 0.0466
-6.500 -0.5955 0.05657 0.05274 -0.0172 1.0000 0.0483
-6.250 -0.5927 0.05383 0.04980 -0.0147 1.0000 0.0513
-6.000 -0.5961 0.05184 0.04706 -0.0104 1.0000 0.0550
-5.750 -0.5866 0.04721 0.04266 -0.0097 1.0000 0.0570
-5.500 -0.5760 0.04500 0.04045 -0.0079 1.0000 0.0595
-5.250 -0.5644 0.04284 0.03808 -0.0058 1.0000 0.0637
-5.000 -0.5553 0.04006 0.03480 -0.0031 1.0000 0.0697
-4.750 -0.5285 0.02565 0.02086 -0.0017 1.0000 0.0721
-4.500 -0.5142 0.02375 0.01879 0.0001 1.0000 0.0775
-4.250 -0.5092 0.03336 0.02767 0.0016 1.0000 0.0858
-4.000 -0.4923 0.03197 0.02594 0.0034 1.0000 0.0980
-3.750 -0.4726 0.02986 0.02388 0.0043 1.0000 0.1040
-3.500 -0.4353 0.02503 0.01785 0.0078 1.0000 0.0520
-3.250 -0.4075 0.02216 0.01450 0.0089 1.0000 0.0453
-3.000 -0.3814 0.02122 0.01322 0.0102 1.0000 0.0430
-2.750 -0.3560 0.02029 0.01217 0.0110 1.0000 0.0417
-2.500 -0.3296 0.01880 0.01057 0.0116 1.0000 0.0411
-2.250 -0.3041 0.01781 0.00950 0.0122 1.0000 0.0412
-2.000 -0.2793 0.01706 0.00870 0.0130 1.0000 0.0418
-1.750 -0.2548 0.01609 0.00775 0.0136 1.0000 0.0433
-1.500 -0.2309 0.01549 0.00721 0.0142 1.0000 0.0482
-1.250 -0.1960 0.01515 0.00683 0.0127 0.9974 0.0539
-1.000 -0.0848 0.01205 0.00711 -0.0036 1.0000 1.0000
-0.750 -0.0631 0.01215 0.00706 -0.0027 0.9992 1.0000
-0.500 0.0184 0.01230 0.00702 -0.0141 0.9872 1.0000
-0.250 0.1403 0.01194 0.00651 -0.0332 0.9702 1.0000
0.000 0.1850 0.01181 0.00633 -0.0368 0.9620 1.0000
0.250 0.2468 0.01153 0.00602 -0.0438 0.9569 1.0000
0.500 0.2853 0.01138 0.00587 -0.0459 0.9486 1.0000
0.750 0.3330 0.01107 0.00556 -0.0496 0.9412 1.0000
1.000 0.3618 0.01092 0.00541 -0.0494 0.9295 1.0000
1.250 0.3890 0.01074 0.00525 -0.0486 0.9170 1.0000
1.500 0.4131 0.01055 0.00507 -0.0471 0.9027 1.0000
1.750 0.4349 0.01033 0.00486 -0.0450 0.8861 1.0000
2.000 0.4551 0.01011 0.00464 -0.0425 0.8661 1.0000
2.250 0.4754 0.00986 0.00439 -0.0401 0.8409 1.0000
2.500 0.4955 0.00965 0.00419 -0.0378 0.8002 1.0000
2.750 0.5122 0.00959 0.00341 -0.0337 0.6242 1.0000
3.000 0.5263 0.01089 0.00365 -0.0310 0.4290 1.0000
3.250 0.5444 0.01186 0.00401 -0.0295 0.3263 1.0000
3.500 0.5656 0.01248 0.00434 -0.0285 0.2864 1.0000
3.750 0.5882 0.01295 0.00467 -0.0276 0.2654 1.0000
4.000 0.6110 0.01338 0.00503 -0.0267 0.2511 1.0000
4.250 0.6339 0.01378 0.00536 -0.0259 0.2387 1.0000
4.500 0.6568 0.01417 0.00569 -0.0250 0.2269 1.0000
4.750 0.6794 0.01460 0.00602 -0.0242 0.2159 1.0000
5.000 0.7029 0.01486 0.00637 -0.0234 0.2064 1.0000
5.250 0.7258 0.01526 0.00675 -0.0226 0.1976 1.0000
5.500 0.7484 0.01562 0.00709 -0.0217 0.1885 1.0000
5.750 0.7714 0.01593 0.00749 -0.0209 0.1797 1.0000
6.000 0.7937 0.01635 0.00791 -0.0200 0.1706 1.0000
6.250 0.8158 0.01665 0.00825 -0.0190 0.1595 1.0000
6.500 0.8375 0.01692 0.00857 -0.0180 0.1454 1.0000
6.750 0.8591 0.01718 0.00891 -0.0169 0.1255 1.0000
7.000 0.8801 0.01759 0.00928 -0.0157 0.1042 1.0000
7.250 0.9000 0.01825 0.00987 -0.0143 0.0910 1.0000
7.500 0.9203 0.01896 0.01064 -0.0130 0.0834 1.0000
7.750 0.9385 0.02001 0.01162 -0.0114 0.0780 1.0000
8.000 0.9591 0.02077 0.01253 -0.0101 0.0741 1.0000
8.250 0.9789 0.02158 0.01342 -0.0087 0.0703 1.0000
8.500 0.9980 0.02282 0.01465 -0.0074 0.0673 1.0000
8.750 1.0184 0.02425 0.01621 -0.0063 0.0653 1.0000
9.000 1.0386 0.02541 0.01757 -0.0050 0.0637 1.0000
9.250 1.0581 0.02668 0.01905 -0.0036 0.0618 1.0000
9.500 1.0760 0.02768 0.02021 -0.0021 0.0590 1.0000
9.750 1.0929 0.02916 0.02168 -0.0010 0.0554 1.0000
10.000 1.1063 0.03030 0.02312 0.0011 0.0524 1.0000
10.250 1.1204 0.03083 0.02381 0.0030 0.0486 1.0000
10.500 1.1347 0.03175 0.02472 0.0046 0.0453 1.0000
10.750 1.1425 0.03405 0.02730 0.0070 0.0426 1.0000
11.000 1.1515 0.03503 0.02858 0.0096 0.0395 1.0000
11.250 1.1605 0.03589 0.02953 0.0119 0.0360 1.0000
11.500 1.1578 0.03902 0.03287 0.0151 0.0330 1.0000
11.750 1.1555 0.04037 0.03455 0.0190 0.0302 1.0000
12.000 1.1549 0.04139 0.03567 0.0223 0.0279 1.0000
12.250 1.1564 0.04278 0.03700 0.0247 0.0261 1.0000
12.500 1.1399 0.04644 0.04093 0.0280 0.0251 1.0000
12.750 1.1286 0.04895 0.04376 0.0304 0.0243 1.0000
13.000 1.1141 0.05237 0.04745 0.0319 0.0237 1.0000
13.250 1.0967 0.05656 0.05190 0.0323 0.0233 1.0000
13.500 1.0766 0.06170 0.05729 0.0312 0.0232 1.0000
13.750 1.0540 0.06819 0.06402 0.0280 0.0233 1.0000
14.000 1.0285 0.07645 0.07248 0.0225 0.0237 1.0000
14.250 1.0006 0.08636 0.08255 0.0157 0.0244 1.0000
14.500 0.9700 0.09708 0.09337 0.0092 0.0252 1.0000
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Polar data table (+)
Polar graphs
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