NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 50,000 Max Cl/Cd: 22.3 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0011sc-il-50000-n5.txt Download as CSV file: xf-n0011sc-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6345 0.10126 0.09279 -0.0380 1.0000 0.0666
-11.250 -0.6501 0.09411 0.08565 -0.0416 1.0000 0.0663
-11.000 -0.6743 0.08712 0.07866 -0.0449 1.0000 0.0660
-10.750 -0.6998 0.08143 0.07292 -0.0462 1.0000 0.0657
-10.500 -0.7293 0.07660 0.06801 -0.0455 1.0000 0.0655
-10.250 -0.7560 0.07283 0.06415 -0.0428 1.0000 0.0653
-10.000 -0.7830 0.06973 0.06093 -0.0384 1.0000 0.0652
-9.750 -0.8069 0.06681 0.05788 -0.0334 1.0000 0.0651
-9.500 -0.8275 0.06362 0.05447 -0.0285 1.0000 0.0653
-9.250 -0.8445 0.06046 0.05104 -0.0236 1.0000 0.0657
-9.000 -0.8571 0.05742 0.04768 -0.0188 1.0000 0.0661
-8.750 -0.8657 0.05449 0.04438 -0.0141 1.0000 0.0665
-8.500 -0.8685 0.05172 0.04130 -0.0100 1.0000 0.0670
-8.250 -0.8630 0.04949 0.03892 -0.0070 1.0000 0.0678
-8.000 -0.8551 0.04762 0.03691 -0.0042 1.0000 0.0692
-7.750 -0.8472 0.04576 0.03486 -0.0013 1.0000 0.0708
-7.500 -0.8392 0.04377 0.03259 0.0017 1.0000 0.0728
-7.250 -0.8301 0.04166 0.03007 0.0048 1.0000 0.0751
-7.000 -0.8176 0.03958 0.02756 0.0075 1.0000 0.0770
-6.750 -0.8005 0.03803 0.02599 0.0091 1.0000 0.0793
-6.500 -0.7836 0.03667 0.02450 0.0110 1.0000 0.0826
-6.250 -0.7650 0.03520 0.02273 0.0127 1.0000 0.0867
-6.000 -0.7436 0.03375 0.02120 0.0139 1.0000 0.0903
-5.750 -0.7227 0.03262 0.02001 0.0151 1.0000 0.0952
-5.500 -0.6990 0.03147 0.01867 0.0161 1.0000 0.1015
-5.250 -0.6762 0.03045 0.01771 0.0169 1.0000 0.1081
-5.000 -0.6514 0.02948 0.01666 0.0176 1.0000 0.1170
-4.750 -0.6270 0.02862 0.01574 0.0183 1.0000 0.1282
-4.500 -0.6030 0.02775 0.01494 0.0190 1.0000 0.1416
-4.250 -0.5804 0.02693 0.01416 0.0199 1.0000 0.1597
-4.000 -0.5601 0.02605 0.01346 0.0211 1.0000 0.1823
-3.750 -0.5413 0.02516 0.01279 0.0226 1.0000 0.2164
-3.500 -0.5247 0.02416 0.01218 0.0245 1.0000 0.2703
-3.250 -0.5122 0.02297 0.01163 0.0271 1.0000 0.3628
-3.000 -0.3876 0.02303 0.01371 0.0127 1.0000 0.8057
-2.750 -0.3527 0.02398 0.01445 0.0132 1.0000 0.8695
-2.500 -0.2997 0.02503 0.01525 0.0098 1.0000 0.9147
-2.250 -0.2340 0.02580 0.01574 0.0032 1.0000 0.9492
-2.000 -0.1551 0.02607 0.01575 -0.0068 1.0000 0.9778
-1.750 -0.0778 0.02585 0.01530 -0.0173 1.0000 1.0000
-1.500 -0.0670 0.02561 0.01500 -0.0149 1.0000 1.0000
-1.250 -0.0561 0.02541 0.01475 -0.0124 1.0000 1.0000
-1.000 -0.0450 0.02526 0.01456 -0.0100 1.0000 1.0000
-0.750 -0.0338 0.02514 0.01440 -0.0075 1.0000 1.0000
-0.500 -0.0226 0.02505 0.01430 -0.0050 1.0000 1.0000
-0.250 -0.0113 0.02500 0.01423 -0.0025 1.0000 1.0000
0.000 0.0000 0.02498 0.01421 0.0000 1.0000 1.0000
0.250 0.0113 0.02500 0.01423 0.0025 1.0000 1.0000
0.500 0.0226 0.02505 0.01429 0.0050 1.0000 1.0000
0.750 0.0339 0.02513 0.01440 0.0075 1.0000 1.0000
1.000 0.0450 0.02525 0.01455 0.0100 1.0000 1.0000
1.250 0.0561 0.02541 0.01475 0.0124 1.0000 1.0000
1.500 0.0670 0.02560 0.01500 0.0149 1.0000 1.0000
1.750 0.0779 0.02584 0.01529 0.0173 1.0000 1.0000
2.000 0.1548 0.02606 0.01574 0.0068 0.9779 1.0000
2.250 0.2356 0.02578 0.01572 -0.0035 0.9488 1.0000
2.500 0.2997 0.02501 0.01522 -0.0098 0.9142 1.0000
2.750 0.3528 0.02397 0.01444 -0.0132 0.8696 1.0000
3.000 0.3865 0.02305 0.01373 -0.0126 0.8070 1.0000
3.250 0.5122 0.02297 0.01163 -0.0271 0.3631 1.0000
3.500 0.5247 0.02415 0.01217 -0.0245 0.2709 1.0000
3.750 0.5412 0.02515 0.01279 -0.0226 0.2167 1.0000
4.000 0.5600 0.02604 0.01345 -0.0211 0.1829 1.0000
4.250 0.5803 0.02692 0.01415 -0.0199 0.1595 1.0000
4.500 0.6029 0.02775 0.01493 -0.0190 0.1414 1.0000
4.750 0.6268 0.02861 0.01574 -0.0183 0.1278 1.0000
5.000 0.6513 0.02947 0.01665 -0.0176 0.1170 1.0000
5.250 0.6762 0.03045 0.01771 -0.0169 0.1079 1.0000
5.500 0.6990 0.03146 0.01866 -0.0160 0.1015 1.0000
5.750 0.7229 0.03264 0.02003 -0.0151 0.0952 1.0000
6.000 0.7435 0.03375 0.02119 -0.0139 0.0902 1.0000
6.250 0.7650 0.03520 0.02274 -0.0127 0.0867 1.0000
6.500 0.7838 0.03670 0.02454 -0.0110 0.0826 1.0000
6.750 0.8004 0.03803 0.02598 -0.0091 0.0792 1.0000
7.000 0.8175 0.03958 0.02755 -0.0076 0.0769 1.0000
7.250 0.8297 0.04169 0.03012 -0.0048 0.0749 1.0000
7.500 0.8391 0.04377 0.03258 -0.0017 0.0727 1.0000
7.750 0.8472 0.04574 0.03484 0.0013 0.0708 1.0000
8.000 0.8559 0.04747 0.03673 0.0041 0.0688 1.0000
8.250 0.8633 0.04944 0.03885 0.0070 0.0677 1.0000
8.500 0.8690 0.05169 0.04125 0.0099 0.0669 1.0000
8.750 0.8645 0.05455 0.04446 0.0143 0.0664 1.0000
9.000 0.8564 0.05748 0.04775 0.0189 0.0660 1.0000
9.250 0.8434 0.06052 0.05111 0.0237 0.0656 1.0000
9.500 0.8265 0.06363 0.05449 0.0286 0.0652 1.0000
9.750 0.8067 0.06681 0.05788 0.0334 0.0651 1.0000
10.000 0.7811 0.06976 0.06098 0.0386 0.0650 1.0000
10.250 0.7533 0.07295 0.06428 0.0429 0.0651 1.0000
10.500 0.7265 0.07678 0.06820 0.0455 0.0653 1.0000
10.750 0.6974 0.08172 0.07322 0.0461 0.0656 1.0000
11.000 0.6732 0.08734 0.07888 0.0447 0.0660 1.0000
11.250 0.6510 0.09407 0.08561 0.0416 0.0663 1.0000
11.500 0.6351 0.10128 0.09281 0.0379 0.0666 1.0000
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Polar data table (+)
Polar graphs
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