NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 200,000 Max Cl/Cd: 39.19 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0011sc-il-200000-n5.txt Download as CSV file: xf-n0011sc-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA/LANGLEY SYMMETRICAL
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8375 0.07160 0.06689 -0.0550 1.0000 0.0261
-13.250 -0.8984 0.06026 0.05517 -0.0605 1.0000 0.0258
-13.000 -0.9259 0.05550 0.05019 -0.0602 1.0000 0.0258
-12.750 -0.9482 0.05194 0.04642 -0.0582 1.0000 0.0260
-12.500 -0.9709 0.04865 0.04290 -0.0548 1.0000 0.0261
-12.250 -0.9881 0.04614 0.04018 -0.0508 1.0000 0.0262
-12.000 -1.0028 0.04398 0.03780 -0.0462 1.0000 0.0264
-11.750 -1.0167 0.04201 0.03561 -0.0410 1.0000 0.0266
-11.500 -1.0283 0.04034 0.03372 -0.0357 1.0000 0.0268
-11.250 -1.0388 0.03881 0.03198 -0.0300 1.0000 0.0270
-11.000 -1.0473 0.03734 0.03028 -0.0243 1.0000 0.0272
-10.750 -1.0501 0.03577 0.02845 -0.0196 1.0000 0.0275
-10.500 -1.0494 0.03424 0.02666 -0.0153 1.0000 0.0278
-10.250 -1.0448 0.03289 0.02509 -0.0116 1.0000 0.0281
-10.000 -1.0363 0.03182 0.02396 -0.0086 1.0000 0.0284
-9.750 -1.0271 0.03090 0.02297 -0.0056 1.0000 0.0288
-9.500 -1.0169 0.02995 0.02194 -0.0027 1.0000 0.0291
-9.250 -1.0061 0.02908 0.02097 0.0002 1.0000 0.0296
-9.000 -0.9943 0.02817 0.01995 0.0029 1.0000 0.0301
-8.750 -0.9817 0.02733 0.01899 0.0055 1.0000 0.0308
-8.500 -0.9682 0.02650 0.01801 0.0081 1.0000 0.0317
-8.250 -0.9539 0.02571 0.01704 0.0105 1.0000 0.0325
-8.000 -0.9399 0.02492 0.01623 0.0129 1.0000 0.0332
-7.750 -0.9254 0.02429 0.01559 0.0152 1.0000 0.0339
-7.500 -0.9103 0.02366 0.01492 0.0175 1.0000 0.0346
-7.250 -0.8949 0.02301 0.01421 0.0198 1.0000 0.0356
-7.000 -0.8769 0.02238 0.01348 0.0216 0.9997 0.0367
-6.750 -0.8516 0.02173 0.01275 0.0218 0.9981 0.0379
-6.500 -0.8260 0.02118 0.01221 0.0218 0.9961 0.0393
-6.250 -0.7988 0.02074 0.01174 0.0216 0.9943 0.0414
-6.000 -0.7740 0.02026 0.01118 0.0221 0.9923 0.0434
-5.750 -0.7496 0.01974 0.01070 0.0225 0.9900 0.0455
-5.500 -0.7232 0.01933 0.01026 0.0225 0.9877 0.0480
-5.250 -0.6959 0.01894 0.00985 0.0224 0.9857 0.0512
-5.000 -0.6691 0.01858 0.00951 0.0223 0.9839 0.0550
-4.750 -0.6457 0.01819 0.00910 0.0231 0.9808 0.0590
-4.500 -0.6200 0.01786 0.00879 0.0233 0.9780 0.0644
-4.250 -0.5926 0.01752 0.00850 0.0232 0.9757 0.0710
-4.000 -0.5633 0.01724 0.00823 0.0227 0.9738 0.0792
-3.750 -0.5402 0.01692 0.00797 0.0236 0.9704 0.0896
-3.500 -0.5157 0.01660 0.00772 0.0241 0.9669 0.1032
-3.250 -0.4885 0.01629 0.00752 0.0241 0.9642 0.1231
-3.000 -0.4592 0.01597 0.00735 0.0235 0.9619 0.1497
-2.750 -0.4356 0.01561 0.00717 0.0242 0.9585 0.1855
-2.500 -0.4145 0.01521 0.00699 0.0255 0.9539 0.2319
-2.250 -0.3902 0.01470 0.00682 0.0259 0.9505 0.3022
-2.000 -0.3667 0.01402 0.00665 0.0265 0.9477 0.4105
-1.750 -0.3609 0.01325 0.00647 0.0312 0.9404 0.5343
-1.500 -0.3393 0.01244 0.00652 0.0329 0.9371 0.7111
-1.250 -0.2128 0.01316 0.00777 0.0126 0.9502 0.8573
-1.000 -0.1685 0.01354 0.00815 0.0096 0.9490 0.8816
-0.750 -0.1284 0.01383 0.00842 0.0075 0.9473 0.8977
-0.500 -0.0978 0.01411 0.00869 0.0074 0.9420 0.9101
-0.250 -0.0570 0.01448 0.00906 0.0052 0.9389 0.9226
0.000 -0.0003 0.01480 0.00939 0.0000 0.9352 0.9352
0.250 0.0573 0.01447 0.00905 -0.0053 0.9225 0.9388
0.500 0.0979 0.01411 0.00869 -0.0074 0.9099 0.9419
0.750 0.1288 0.01384 0.00843 -0.0076 0.8984 0.9473
1.000 0.1684 0.01354 0.00814 -0.0096 0.8814 0.9490
1.250 0.2125 0.01317 0.00778 -0.0125 0.8577 0.9503
1.500 0.3393 0.01243 0.00653 -0.0329 0.7118 0.9371
1.750 0.3609 0.01325 0.00647 -0.0312 0.5345 0.9404
2.000 0.3669 0.01401 0.00665 -0.0266 0.4114 0.9477
2.250 0.3901 0.01470 0.00681 -0.0259 0.3024 0.9505
2.500 0.4146 0.01520 0.00698 -0.0255 0.2328 0.9539
2.750 0.4356 0.01561 0.00717 -0.0242 0.1864 0.9585
3.000 0.4593 0.01597 0.00734 -0.0236 0.1506 0.9619
3.250 0.4885 0.01629 0.00751 -0.0241 0.1221 0.9642
3.500 0.5158 0.01660 0.00772 -0.0242 0.1032 0.9670
3.750 0.5402 0.01692 0.00796 -0.0236 0.0895 0.9704
4.000 0.5633 0.01723 0.00823 -0.0228 0.0793 0.9738
4.250 0.5926 0.01752 0.00849 -0.0233 0.0707 0.9757
4.500 0.6201 0.01785 0.00878 -0.0234 0.0642 0.9781
4.750 0.6456 0.01820 0.00910 -0.0231 0.0588 0.9808
5.000 0.6691 0.01858 0.00950 -0.0223 0.0549 0.9839
5.250 0.6961 0.01893 0.00983 -0.0224 0.0509 0.9858
5.500 0.7232 0.01933 0.01026 -0.0225 0.0480 0.9878
5.750 0.7497 0.01974 0.01070 -0.0225 0.0454 0.9900
6.000 0.7741 0.02026 0.01118 -0.0221 0.0434 0.9923
6.250 0.7989 0.02073 0.01173 -0.0217 0.0412 0.9943
6.500 0.8262 0.02115 0.01219 -0.0219 0.0391 0.9961
6.750 0.8516 0.02174 0.01275 -0.0218 0.0378 0.9981
7.000 0.8770 0.02238 0.01349 -0.0216 0.0365 0.9997
7.250 0.8948 0.02301 0.01421 -0.0198 0.0354 1.0000
7.500 0.9102 0.02365 0.01490 -0.0175 0.0345 1.0000
7.750 0.9252 0.02428 0.01557 -0.0152 0.0338 1.0000
8.000 0.9396 0.02492 0.01622 -0.0129 0.0330 1.0000
8.250 0.9538 0.02569 0.01704 -0.0105 0.0323 1.0000
8.500 0.9681 0.02653 0.01804 -0.0081 0.0316 1.0000
8.750 0.9815 0.02735 0.01901 -0.0055 0.0306 1.0000
9.000 0.9942 0.02819 0.01997 -0.0029 0.0301 1.0000
9.250 1.0060 0.02911 0.02100 -0.0002 0.0296 1.0000
9.500 1.0170 0.02997 0.02196 0.0027 0.0291 1.0000
9.750 1.0271 0.03088 0.02295 0.0056 0.0287 1.0000
10.000 1.0363 0.03183 0.02396 0.0086 0.0284 1.0000
10.250 1.0446 0.03296 0.02517 0.0116 0.0281 1.0000
10.500 1.0494 0.03429 0.02671 0.0153 0.0278 1.0000
10.750 1.0496 0.03584 0.02854 0.0197 0.0275 1.0000
11.000 1.0471 0.03739 0.03033 0.0243 0.0272 1.0000
11.250 1.0391 0.03885 0.03202 0.0299 0.0271 1.0000
11.500 1.0281 0.04039 0.03378 0.0357 0.0268 1.0000
11.750 1.0160 0.04210 0.03570 0.0411 0.0266 1.0000
12.000 1.0027 0.04405 0.03787 0.0462 0.0264 1.0000
12.250 0.9870 0.04630 0.04035 0.0508 0.0263 1.0000
12.500 0.9708 0.04867 0.04292 0.0548 0.0260 1.0000
12.750 0.9502 0.05176 0.04624 0.0580 0.0260 1.0000
13.000 0.9295 0.05514 0.04981 0.0601 0.0257 1.0000
13.250 0.8903 0.06138 0.05634 0.0601 0.0259 1.0000
13.500 0.8395 0.07137 0.06665 0.0551 0.0262 1.0000
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Polar data table (+)
Polar graphs
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